Aircraft

• US 20160376003A1
• Filed: 06/26/2015
• Published: 12/29/2016
• Est. Priority Date: 06/26/2015
• Status: Abandoned Application

• Current Assignee: Yuri Feldman
• Original Assignee: Yuri Feldman
• Inventors: Feldman, Yuri
• Application Number:
  US14/751,180
• Publication Number:
  US 20160376003A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 13/44 overriding of personal controls; with automatic return to inoperative position
• CPC Class Codes: B64C 31/02 Gliders, e.g. sailplanes hang-gliders B64C31/028
• CPC Class Codes: B64C 31/028 Hang-glider-type aircraft; Microlight-type aircraft
• CPC Class Codes: B64C 39/005 about a horizontal transversal axis
• CPC Class Codes: B64D 33/08 of power plant cooling systems cooling of internal-combustion engines per se F01P; cooling of gas-turbine plants or jet-propulsion plants per se F02C, F02K
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: G01P 13/025 indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
• CPC Class Codes: G06F 30/20 Design optimisation, verification or simulation optimisation, verification or simulation of circuit designs G06F30/30
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

Conception introduced for performing powered flight of aircraft by performing work against gravity force, using gliding wing as steady support, namely “flying elevator” conception, and aircraft developed, based on cyclorotor scheme with elaborated steering solution, continuing in flexible handling and control. Said aircraft correctly and optimally implements said conception after presented detailed modeling, simulation and analyzing, having ability for flight with exceptionally high propulsion efficiency, moderate lift to drag ratio and short takeoff and landing. Additionally, it has ability for recuperative descent and deceleration, utilizing direct driving from high torque electrical engines, which can optionally hybridized with combustion engine, and covers speed range up to limits of subsonic flight.

Claims

1. A rotor for powered flight with managed PGS-state comprising:

a rotational domain with generally round shape and generally flat surface face side thereof;

a set of equal wings, equidistantly mounted on periphery of said rotational domain, longitudinally extended from face side thereof outside and parallel to central axis thereof on fixed distance from said axis with ability of rotation around respective axes parallel to said axis, having said respective axes in respective pivot positions relative respective chords of said wings;

an irrotational domain rotationally mount on said rotational domain in respect of said central axis thereof generally on back side thereof with particularly sharing overall volume space of said rotational domain, the irrotational domain used as irrotational tier of setup of said rotor and as reference base for steering said wings in accordance with managed PGS-state;

a central cluster, comprising placed coaxially a central gear and a circular grove, mounted on said irrotational domain toward direction of face side of rotational domain, having axis thereof parallel to central axis of said rotational domain with means for steering said central gear in angular, radial and asimuthal directions relative to said irrotational domain, where each freedom of said steering mapped to steering of pitch, gain and skew respectively, and have a continuation used as steering tier of setup of said rotor, comprising from separated PGS components or their combinations; and

a set of steering elements per each wing includes a pitch gear, having angular position of axis thereof generally directed to axis of respective wing from central axis of said rotational domain, a steering pinion meshed with said pitch gear, a entry gear shared common axis with said steering pinion, upon joining in respective steering cluster, and meshed with central gear of central cluster, having ratio teeth′

number thereof to number of teeth of said central gear equal to ratio of teeth′

number of said steering pinion to number of teeth of said pitch gear, a grove follower inserted to circular grove of central cluster and shared common axis with said entry gear upon joining to said steering cluster, a means for keeping fixed distance between axes of said steering cluster and said pitch gear, and a transmission between said pitch gear to respective wing, providing unitary angular relation between said pitch gear and said wing.

2. The rotor set forth in claim 1 wherein said rotor has features and elements comprising:

a central powering shaft, used as rotational tier of setup of said rotor and belonged to said rotational domain;

a flanged hub, fixed on said central powering shaft;

a round faceplate belonged to said rotational domain and represents face side thereof, providing mounting basement for said wings, the round faceplate fixedly connected on center of inside thereof to flanged side of said flanged hub, having coaxial relation with said central powering shaft;

a back-ring belonged to said rotational domain, coaxially mounted on inside of said faceplate on fixed distance there from, imposing axial position of said central cluster between axial position thereof and said faceplate;

a steady base with flange generally represents said irrotational domain, fixed on said central powering shaft on fixed distance from said back-ring with freedom of rotation in respect of said central powering shaft;

a round base of each said wing as integral element thereof, entered in respective correspondent hole of said faceplate, having face side thereof generally on same level with face level of said face plate, with fillet interface on each side of said wing and smooth transition of leading edge of said wing to rim thereof;

a shaft per each said pitch gear, on which said pitch gear fixed, the shaft rotationally mounted on ends thereof between said faceplate and said back-ring; and

a shell per each said pitch gear, which represents said means for keeping fixed distance between axes of said steering cluster and said pitch gear, the shell rotationally fixed on said shaft of respective pitch gear and provides full rotational support for respective steering cluster, becoming with all said elements of content thereof an earring assembly.

3. The rotor set forth in claim 2 wherein each transmission between related pitch gear and respective wing comprises:

a bevel gear with substantially high diameter, fixedly mounted on base of wing;

a bevel pinion meshed with said bevel gear;

a shaft-mounted cluster of a pinion, meshed with respective pitch gear, and a miter gear, where ratio of teeth′

number of said pitch gear to teeth′

number of said pinion equal to ratio of teeth number of said bevel gear to ratio of teeth number of said bevel pinion, and which shaft rotationally mounted on ends thereof between said faceplate and said back-ring;

a separated miter gear meshed with miter gear of shaft-mounted cluster; and

a transmission shaft, on which ends said separated miter gear and said bevel pinion fixed, and having support axis thereof in radial and axial directions in respect to said faceplate.

4. The rotor set forth in claim 3 wherein a set of equal ribs, which number equal to number of said rotor wings, used as distributed separation support of said back-ring on said faceplate, which members equidistantly placed around outer rim of said back-ring, providing rotational support for said transmission shafts from sides of said separated miter gears also.

5. The rotor set forth in claim 3 wherein a set of equal wing sockets of cup-like shape, which number equal to number of said wings, equidistantly mounted on periphery of said faceplate and used for rotational support of said wings and for rotational support for said transmission shafts from sides of said bevel pinions.

6. The rotor set forth in claim 3 wherein a set of screws used for fixing said bevel gear on base of wing, which placed around periphery of inside teeth area of said bevel gear, without protruding from level of the area.

7. The rotor set forth in claim 5 wherein a wing owned shaft of each said wing fixed inside said wing and protrudes from center of respective round base in direction opposite to said wing, servicing as pivot axis of said wing, and wherein each of wing sockets has a set of parts assigned thereto and related to support and installation of respective wing comprising:

a primary thrust bearing, placed between bottom of said wing socket and periphery of inside teeth area of bevel gear of said wing;

a radial needle bearing, placed inside of a central hole of said wing socket;

a tubular flange, dressed over shaft owned by said wing, having a tubular part thereof inside of said radial needle bearing and a flanged part outside of said wing socket;

a secondary thrust bearing, placed outside between bottom of said wing socket and the flanged part of said tubular flange; and

a nut screwed from outside on a threaded end of said shaft over the flange part of said tubular flange.

8. The rotor set forth in claim 5 wherein a set of bridges used for connect pairs of neighbored wing sockets, where each said bridge is a segment of plate, having mating rims thereof complementary to outer shape of said wing socket on mating interface, and oriented parallel to said faceplate upon mounting thereof on said wing sockets.

9. The rotor set forth in claim 2 wherein an irrotational shifting base mounted on said steady base as interface between said central cluster and means for steering thereof in radial and asimuthal directions relative to said steady base, and with thereof own means of angular steering of said central cluster, where said own means have continuation for pitch steering interface of said steering tier of setup.

10. The rotor set forth in claim 9 wherein steering tier of setup of rotor represents thereof components by mechanical means comprising:

a pitch outer shaft, which rotation used for change pitch of said rotor;

a gain outer shaft, which rotation used for change gain of said rotor in linear form; and

a skew outer shaft, which rotation used for change skew of said rotor or skew and gain simultaneously.

11. The rotor set forth in claim 10 wherein said central cluster includes a internal gear coaxially placed thereon, and said rotor further comprises:

a pitch flanged bracket, mounted on said shifting base on flange side thereof upon inserting through respective pitch hole of steady base of said rotor, and having a worm support bracket as other side thereof;

a pitch steering shaft, mounted inside said pitch flanged bracket with freedom of rotation;

a pitch pinion, fixed on inner end of said pitch steering shaft and meshed with said internal gear;

a pitch worm gear, fixed on outer end of said pitch steering shaft;

a telescopic universal joint, which outer shaft mounted on said steady base with freedom of rotation and used as pitch outer shaft of steering tier of setup, and which inner shaft mounted on said worm support bracket with freedom of rotation; and

a pitch worm, fixed on said inner shaft of telescopic universal joint and meshed with said pitch worm gear.

12. The rotor set forth in claim 9 wherein rotational support of said central cluster on said shifting base provides by a system comprising:

a radial bearing, placed between said shifting base and said central cluster;

a closing flange coaxially mounted on said shifting base from side of said faceplate; and

a thrust bearing, placed between said central cluster and said closing flange.

13. The rotor set forth in claim 9 wherein an irrotational fixation on fixed axial position for said shifting base relative to said steady base provides by a retaining system comprising:

a set of three radial rods, where each mounted by inner end thereof on said flange of steady base with radial and normal orientation relative to central axis of said rotor between said steady base and said shifting base and being fixed by outer end thereof on said steady base, where two of said radial rods oriented exactly in counter-direction, and third of said radial rods oriented by right angle to both others, becoming central radial rod;

a set of three tangential rods, where each mounted by ends thereof on said shifting base below of respective radial rod and with right angle orientation of axis thereof to axis of respective radial rod; and

a set of three cross-holes bearings, where in respective holes of each said bearing respective pair of said radial rod and said tangential rod inserted, having ability of free axial movement.

14. The rotor set forth in claim 13 wherein said tangential rods placed between said shifting base and said central cluster, and said shifting base has three side slots, which provide clearance for respective cross-holes bearings.

15. The rotor set forth in claim 13 wherein one of said cross-hole bearings has two crampons as symmetrical extensions along direction of respective tangential rod, and said crampons inserted in two respective saddles fixed on said shifting base, extending retaining base of tangential retaining component of said cross-hole bearing.

16. The rotor set forth in claim 10 wherein means of steering of shifting base are provided by a Gain-Skew-node (GS-node), which mounted on said steady base upon inserting kernel part thereof, referenced as GS-variator, in respective hole of said steady base, and said GS-variator provides direct steering interface to said shifting base and comprises:

a flange, which has generally round shape, providing desired space for other rotated elements in its interior, and used also for mounting said entire GS-node on said steady base by mounting base thereof, which axial direction relative to said steady base from said shifting base referenced as bottom direction;

a skew worm gear, mounted inside and below of said flange on fixed distance with freedom of rotation;

a toothed rack, mounted on said skew worm gear with tangential orientation of toothed side thereof on fixed distance from center of said skew worm gear with freedom of movement along teeth thereof;

a gain steering shaft, mounted on said flange coaxially with said flange with freedom of rotation;

a gain gear, fixed on said gain steering shaft and meshed with said toothed rack;

a steering lead, fixed on said toothed rack, having a round steering pin, inserted in correspondent hole of said shifting base with means of rotation, where said steering pin has coaxial relation with axis of said skew worm gear for neutral state of gain;

a gain worm gear fixed on said gain steering shaft in upper outside position from said flange;

a gain inner shaft, mounted on said flange with freedom of rotation, which can be used as gain outer shaft of steering tier of setup, when using of simultaneously change of skew and gain by corresponded skew outer shaft is permissible;

a gain worm fixed on said gain inner shaft and meshed with said gain worm gear;

a skew steering shaft, mounted on said flange with freedom of rotation, which can be used as skew outer shaft of steering tier of setup, when placement of axis of said skew outer shaft between said steady base and said shifting base in axial direction of said rotor is permissible; and

a skew worm fixed on said skew steering shaft and meshed with said skew worm gear.

17. The rotor set forth in claim 16 wherein said GS-variator has compact placement in axial direction by using features and elements comprising:

a rectangular dip on upper side of said skew worm gear in which said toothed rack placed moveable, slipping on bottom and toothed-opposite surfaces thereof;

a hole in said rectangular dip in which said steering lead inserted from bottom side and fixed on said toothed rack, having a slipping ledge, which slips over bottom surface of said skew worm gear, providing fixation for said toothed rack and for itself in axial direction;

a round dip on upper side of said skew worm gear in which said gain gear inserted keeping correct vertical alignment with said toothed rack;

a retaining ring, which coaxially and fixedly mounted on said skew worm gear, the retaining ring has a retaining rim on upper flange thereof;

a flanged bearing, which inserted coaxially in central hole of said skew worm gear from up, the flanged bearing provides radial and bottom axial supports for said gain steering shaft relative to said skew worm gear and laid under said gain gear;

a intermediate ring, which coaxially and fixedly mounted on said flange, the intermediate ring has two retaining rims on bottom flange thereof;

a outer bearing, which placed between said retaining ring and said intermediate ring, providing radial and bottom-axial supports for said skew worm gear, using said retaining rims of both said rings; and

a inner bearing, which placed between said intermediate ring and hub of said gain gear, completing radial and axial supports for said gain steering shaft and said skew worm gear.

18. The rotor set forth in claim 16 wherein said GS-variator permits simplified manufacturing and more convenient placement of said skew outer shaft of steering tier of setup by using elements comprising:

a skew outer shaft, which implements said skew outer shaft of steering tier of setup;

a skew bracket, which mounted over mounting base of flange of GS-variator, having flat-sector shape of mounting interface thereof with inner radius correspondent to related radius of said flange, the skew bracket used for support said skew steering shaft on ends thereof, so manufacturing of said flange without said support function can utilize turning operations, and additionally the skew bracket used for support said skew outer shaft on inner end and on other entry side thereof, placing axis thereof above said steady base and in parallel orientation to axis of said gain inner shaft and said skew steering shaft too; and

two meshed gears, where one of these gears fixed on said skew steering shaft outside of said skew bracket, and other gear fixed on said skew outer shaft near inner end thereof inside of said skew bracket.

19. The rotor set forth in claim 16 wherein said GS-node has a SG-compensator, which permits completely decompose gain and skew components of entire PGS-state, by providing rotation from said skew steering shaft to said gain inner shaft by a gear means and means of differential transmission, where rotation transmitted to said gain steering shaft provides movement of said toothed rack, compensating respective movement induced by rotation of said skew worm gear, and where other side of said means of differential transmission accepts rotation from said gain outer shaft of steering tier of setup.

20. The rotor set forth in claim 19 wherein said SG-compensator composed with a gain-handling reducer for aligning rotational speed of said gain outer shaft and pitch outer shaft of said steering tier of setup in relation to changing of correspondent components of PGS-state to ratios optimal for main flight operations, the reducer has two stages with coaxial placement of said gain outer shaft and said gain inner shaft, and said means of differential transmission placed between them, and with said composition said SG-compensator comprises:

a gain bracket, which mounted over mounting base of flange of GS-variator, having flat-sector shape of mounting interface thereof with inner radius correspondent to related radius of said flange, the gain bracket used for support all shafts of entire SG-compensator, except transverse shaft of said means of differential transmission, the gain bracket also supports end of said gain inner shaft and said skew steering shaft;

a gain outer shaft, which implements said gain outer shaft of steering tier of setup, the gain outer shaft supported by said gain bracket on inner end and other entry side thereof in coaxial relation with gain inner shaft;

an outer reduction pinion fixed on said gain outer shaft inside of said gain bracket;

an outer reduction gear meshed with said outer reduction pinion and has rotational support over hub thereof in radial and inner axial directions by a bearing inserted in said gain bracket from outside;

an outer miter gear fixed in hub of said outer reduction gear;

an inner miter gear;

an adapter has rotational support on tail thereof by said gain bracket and provides fixation for said inner miter gear, supporting it in coaxial relation to said outer miter gear;

an inner reduction pinion fixed on said tail of said adapter;

an inner reduction gear meshed with said inner reduction pinion and fixed on said gain inner shaft;

a transverse shaft has a rectangular section in center thereof with a cross-hole to axis thereof and a threaded hole in perpendicular direction;

two intermediate miter gears placed on ends of said transverse shaft with freedom of rotation and with support in outer axial directions, these miter gears meshed with said outer and inner miter gears in differential'"'"'s relation;

a flanged bearing inserted in central hole of said outer reduction gear from outside;

a compensating shaft inserted to said flanged bearing up to limit of tail thereof, the compensating shaft has also rotational support on outer end thereof in said gain bracket, completing rotational support of said outer reduction gear, and tail thereof inserted in said cross-hole of transverse shaft and in central holes of said outer and inner miter gears;

a setscrew screwed into said threaded hole of transverse shaft and fixes said compensating shaft inside of said transverse shaft, creating a spider of the completed differential;

a compensating gear fixed on said compensating shaft;

a compensating pinion fixed on said skew steering shaft; and

a intermediate gear mounted on said gain bracket with freedom of rotation and meshed with said compensating gear and said compensating pinion.

21. The rotor set forth in claim 1 wherein an end rotor support ring mounted on ends of said wings with freedom of rotation of each said wing in connection thereof with the end rotor support ring by using features and elements comprising:

a convex shape of cross-section of said end rotor support ring in outside axial direction, which provides enough volume for place other elements inside of said end rotor support ring, having said shape of the cross-section airflow friendly;

a flat inner side in axial direction of said end rotor support ring;

a substantially big and flat end base of each said wing, which permits having tight interface with inner flat side of said end rotor support ring;

an end wing fairing of each said wing, which provides enough volume for place other elements inside of thereof and keeps airflow friendly cross-section between transition thereof from airfoil of said wing to said flat end base, having additional protruding in direction of leading edge thereof and said wing;

a set of equal step-holes equidistantly spaced around center-line of said end rotor support ring with number equal to number of said wings, having generally three stages of said stepping, where stage with highest diameter of said step-hole placed on inner flat side of said end rotor support ring;

an end wing tubular flange inserted by flanged side thereof to middle stage of each said step-hole;

an end wing secondary thrust bearing laid on wing'"'"'s side of each said end wing tubular flange;

an end wing radial needle bearing, dressed over tubular part of each said end wing tubular flange after said end wing secondary thrust bearing;

an end wing adapting flange laid over each said end wing secondary thrust bearing, entering by centering ring thereof in outer stage of said step-hole and fixed around perimeter thereof to said end rotor support ring by screws, having said end wing radial needle bearing inside of center hole thereof without possibility of fall out, upon closing it by under-flanged part thereof;

a step-hole exists in said flat end base of each wing, centered around pivot axis of said wing, having generally three stages of said stepping, where stage with smallest diameter has on continuation thereof a threaded finalizing inside of said wing;

an end wing primary thrust bearing with diameter higher than said end wing secondary thrust bearing laid in middle stage of said step-hole of each wing after said correspondent end wing adapting flange, where last enters in outer stage of said step-hole of wing by area of said screws of fixation thereof and provides additional radial aligning of the bearing by under-flanged part thereof;

an end wing bolt enters from outside of each step-hole of end rotor support ring to said end wing tubular flange and screwed in said threaded finalizing inside of respective wing, having head thereof inside of said step-hole with smallest diameter, the end wing bolt has freedom of rotation inside of said end rotor support ring with said end wing tubular flange altogether;

two setscrews fix each said end wing bolt against unscrewing, using respective setup holes on both sides of said respective end wing fairing; and

an end wing seal enters in outer remainder of each said step-hole and seals its content from environment, having airflow friendly outer surface.

22. The rotor set forth in claim 1 wherein at least one intermediate support ring mounted in midst of said wings with freedom of rotation of each said wing in intersection thereof with said intermediate rotor support ring in respect the ring, and with ability transmit rotational moment from inward to outward linked components of each said wing relative said intermediate support ring by using features and elements comprising:

two flat sides in axial direction of said intermediate rotor support ring;

a substantially big and flat intermediate base of each linked component of each said intersected wing, which permits having tight interface with flat sides of said intermediate rotor support ring;

an intermediate wing fairing of each linked component of each said intersected wing, which provides enough volume for place other elements inside of thereof and keeps airflow friendly cross-section between transition thereof from airfoil of said linked component to said flat intermediate base, having additional protruding in direction of leading edge thereof and said linked component;

a set of equal holes equidistantly spaced around said intermediate rotor support ring with number equal to number of said wings;

a wings'"'"'-link radial needle bearing inserted in each said hole of intermediate rotor support ring and some protruded from both sides of said intermediate rotor support ring;

a wings'"'"'-link adapting flange placed on each side of each hole of said intermediate rotor support ring and centered by said correspondent protruded end of respective wings′

-link radial needle bearing, the wings'"'"'-link adapting flange has a under-flanged part, which closes said wings'"'"'-link radial needle bearing from going out;

a step-hole exists in said flat intermediate base of each linked component of each intersected wing, centered around pivot axis of said linked component, having generally three stages of said stepping, where stage with smallest diameter has on continuation thereof a threaded finalizing inside of said linked component;

a wings'"'"'-link thrust bearing laid in outer stage of said step-hole of each linked component of each intersected wing after respective wings'"'"'-link adapting flange, where last provides additional radial aligning to said bearing by under-flanged part thereof;

a wings'"'"'-link shaft has central part with substantially high diameter, which enters in each said wings'"'"'-link radial needle bearing and in middle stages of step-holes of intermediate bases of correspondent linked components, and has two symmetrical tails of lower diameter with threaded ends, which screwed into said threaded finalizing inside of linked components, having complementary right-left handing of said threaded ends thereof for fine regulation backlash between said intermediate rotor support ring and both components of said intersected wing; and

two setscrews fix each side of each said wings'"'"'-link shaft for transmitting rotation moment, using respective setup holes on both sides of said correspondent intermediate wing fairings, these setscrews also permit using one of linked component as handle for setup and fine regulation of said backlash upon alternated screwing-unscrewing of said setscrews from respective sides of said wings'"'"'-link shaft.

23. The rotor set forth in claim 22 wherein winglets installed as most outer linked components of said wings intersected with said intermediate rotor support rings, having wing fences on ends thereof.

24. The rotor set forth in claim 22 wherein winglets installed as most outer linked components of said wings intersected with said intermediate rotor support rings, having longitudinal sweeping toward leading edges thereof for particular compensating overall negative rotational moments of said wings in high speed flight operations performed with said rotor.

25. The rotor set forth in claim 2 wherein a cross-section of each said wing utilizes a symmetrical airfoil, having substantially low moment coefficient on 0.25 of chord thereof, which used as pivot position, and said wings has trailing edge thereof substantially protruded from rim of said round base of said wing, against having said round base too big.

26. The rotor set forth in claim 1 wherein a cross-section of each said wing utilizes a supercritical airfoil.

27. A rotary wing aircraft generally based on conception for performing powered flight of aircraft by performing work against gravity force, using gliding wing as steady support, namely “

flying elevator”

conception, comprising;

a fuselage, having generally streamlined elongated shape;

handling means installed on said fuselage and used for handling and control of said aircraft;

two stabilators pivotally mounted apart on left and right sides of aft of said fuselage, with ability of control of pitch thereof and connected to respective tier of said handling means;

engine means installed on said fuselage and connected to said handling means on respective tier of said handling means;

energy supply means installed on said fuselage and connected to said engine means and to respective tier of said handling means;

two rotors with managed PGS-state of axially oriented wings thereof and construed in accordance with four gears pitch steering scheme, mounted apart on left and right sides of said fuselage, where each has setup tiers including;

a rotational tier drivable connected to said engine means, an irrotational tier fixedly mounted on respective irrotational element of said aircraft and represented by a steady base of said rotor and a steering tier, which represented by means of managed separated PGS-components or their combinations and connected to respective tier of said handling means; and

locking means used for locking against rotation of said rotational tiers of setup of said rotors upon gliding of said aircraft, these locking means have an irrotational tier thereof mounted on respective irrotational elements of said aircraft, a rotational tier thereof mounted with drivable connectivity to said rotational tiers of setup and a handling tier, which represented by means of switching between locked and non-locked state thereof for said both rotors simultaneously and connected to respective tier of said handling means.

28. The aircraft set forth in claim 27 wherein said steering tier of setup of each said rotor represents thereof components by mechanical means comprising:

a pitch outer shaft, which rotation used for change pitch of said rotor;

a gain outer shaft, which rotation used for change gain of said rotor in linear form; and

a skew outer shaft, which rotation used for change skew of said rotor or skew and gain simultaneously;

and wherein said handling means has pair from servo and encoder per each said outer shaft rotationally connected with respective outer shaft, and used for management thereof.

29. The aircraft set forth in claim 28 wherein tiers of said handling means related to said two stabilators and to said locking means connected to them by respective shafts, having pair from servo and encoder rotationally connected with each said shaft, and wherein said handling means have also an attitude control system, an airstream control system and a stabilator controller, where last can manage pitch of said stabilators upon actuating servo related to said stabilators for keeping desired pitch of said fuselage relative to ground using the attitude control system, or for keeping said fuselage pointed to direction of airstream using the airstream control system (stream following feature), dependently from particular flight operations.

30. The aircraft set forth in claim 29 wherein said engine means comprise two electrical engines respective and drivable connected to said rotational tiers of setup of respective rotors, and wherein energy supply means include set of electrical sources connected to two power circuits respectively and correspondently to these two electrical engines and managed by respective tier of said handling means.

31. The aircraft set forth in claim 30 wherein said power circuit can conduct power for recuperation mechanical energy of said rotors to said electrical sources, said electrical engines can operate for the recuperation, and said electrical sources can receive and store electrical energy in any form.

32. The aircraft set forth in claim 30 wherein said rotational tier of setup of each rotor represented by a central powering shaft placed coaxially with said rotor.

33. The aircraft set forth in claim 32 wherein said central powering shafts of both rotors fixedly connected with each other and said two power circuits have common control.

34. The aircraft set forth in claim 33 wherein tier of said handling means related to electrical engines has a pair from servo and encoder, where said encoder used as primary source for defining target winding speed for said both rotors, and wherein said handling means have also an engine controller, which accept values from said encoder and manages said both power circuits for reflect desired target winding speed of said rotors, having feedback about actual winding speed and keeping rotational moment induced by acceleration of said rotors inside of limits of prescribed constrains.

35. The aircraft set forth in claim 32 wherein said electrical engines have generally disk-like shape with high diameter about of half of said rotor'"'"'s diameter, which permits having high torque, and small thickness, which permits having low weight, and rotational tiers thereof directly coupled with said powering shafts of respective rotors.

36. The aircraft set forth in claim 35 wherein said fuselage has two rotors'"'"' sockets with generally conical shape and with diameter generally about 40 percents higher than height of said fuselage in vicinity thereof and with aligning of outer bases thereof with neighbored levels of said fuselage, in which said two respective rotors inserted from outside of said fuselage up to beginning of wings of said rotors, these rotors'"'"' sockets used as fairings for said rotors, and provide additional rigidness for said fuselage also, and wherein said fuselage has in shape thereof intermediate interfaces along common section borders of said rotors'"'"' sockets and streamlined part of said fuselage for smoothing over said section borders.

37. The aircraft set forth in claim 36 wherein said fuselage has inside thereof on each lateral side a force plate, continuing from fuselage floor in vertical direction up to upper limits of said fuselage and having a big hole coaxial with respective rotor, and vicinity of said hole integrally connected with inner base of conical surface of respective rotor'"'"'s socket, providing additional rigidness for said fuselage, and wherein said electrical engines inserted to said holes from outside of said fuselage and fixed over perimeter of said holes, having a setup flanges over bodies thereof for said fixation, and which bodies used for mounting of said steady bases of rotors.

38. The aircraft set forth in claim 37 wherein said fuselage has sockets for said electrical engines, and each said engine'"'"'s socket comprises:

a socket'"'"'s drum, which is a ring integrally connected to inner side of said force plate of fuselage in coaxial placement to hole of said force plate, having diameter thereof moderate higher than diameter of said respective electrical engine, small thickness and axial length about axial length of protruded part of said engine over said force plate;

a socket'"'"'s back-ring, which has outer diameter equal to outer diameter of said socket'"'"'s drum, small thickness and inner diameter some small than diameter of said electrical engine, the socket'"'"'s back-ring integrally connected to said socket'"'"'s drum over entire perimeter thereof and seals entire air volume between said socket'"'"'s drum and said electrical engine upon additional fixation of inner flange of said electrical engine thereto; and

a remainder of said force plate, created upon integration of said socket'"'"'s drum to said force plate;

and wherein said fuselage has a cooling system per each electrical engine, based on said engine'"'"'s socket, comprising;

an entry airflow window of said engine'"'"'s socket created in upper-forward quadrant of said socket'"'"'s drum;

an air inlet placed over forward streamlined part of said fuselage in interface thereof with said rotor'"'"'s socket after joining thereof with said force plate, and generally has shape of horizontal projection of said entry airflow window to said fuselage;

an air separating plate placed generally horizontal from bottom of said entry airflow window to cylindrical surface of said electrical engine with generally near to tangential relation thereto, having also continuation to forward direction up to bottom of said air inlet, the air separating plate has width equal to distance between said force plate of fuselage and said socket'"'"'s back-ring, disabling to air going underneath;

an air sealing plate placed generally horizontal from top of said air inlet to top of said entry airflow window, having same width as said air separating plate, disabling to air going outside of volume space of said cooling system;

an exit airflow window of said engine'"'"'s socket created in upper-forward quadrant of said socket'"'"'s back-ring under said air separating plate, permitting for warm air go out said engine'"'"'s socket after its turn around said electrical engine;

an air outlet placed over backward streamlined part of said fuselage in interface thereof with said rotor'"'"'s socket after aft limit of said force plate, but more inner in axial direction of said rotor then said air inlet;

an air conduction tube placed inside of said fuselage in direction generally parallel to ceil of said fuselage and to closed vicinity to said ceil toward aft of said fuselage, the air conduction tube has generally rectangular shape in each cross-section thereof, fixed on two opposed segments of said socket'"'"'s back-ring and fixedly connected to said fuselage along perimeter of said air outlet, bypassing warm air and increasing rigidness to said fuselage also.

39. The aircraft set forth in claim 35 wherein said central powering shaft of each said rotor going through center of rotor of respective electrical engine and fixed therein with ability of detaching.

40. The aircraft set forth in claim 39 wherein each electrical engine has a hollow shaft mounted on center of its rotor after insertion tubular part thereof to a correspondent hole in rotor of said electrical engine from inside direction of fuselage, having flanged part thereof referenced as setup flange and fixed to correspondent side of rotor of electrical engine from inside direction also, the hollow shaft has a continuation of tubular part thereof from other side of said setup flange, providing fixation for said central powering shaft inserted in central hole thereof, and the hollow shaft manufactured from high module alloy, permitting using lightweight alloy for remained part of rotor of electrical engine.

41. The aircraft set forth in claim 40 wherein each said hollow shaft has a collet clamp used for fixation said central powering shaft of rotor comprising:

a fine tolerance clamping area with thread on said continuation of tubular part, with a number of end-beginning slots around thereof and with outer end-cone; and

a clamping nut, which screwed over thread of said fine tolerance clamping area and has inner cone correspondent to said outer end-cone of said fine tolerance clamping area.

42. The aircraft set forth in claim 40 wherein each electrical engine has elements related to force accepting interior thereof comprising:

a high load needle bearing, which placed inside of body of said electrical engine and provides radial support to end of said hollow shaft from side of entering said central powering shaft of rotor;

a lid, which closed interior of said electrical engine from inside direction of said fuselage and has a central hole with diameter a bit higher then outer diameter of setup flange of hollow shaft;

a middle load bearing, which placed inside of said lid, having inside diameter thereof generally equal to diameter of central hole of said lid, the middle load bearing provides radial and inner axial support for remained part of rotor of electrical engine; and

a low load bearing, which placed inside of body of said electrical engine, overlapping said high load needle bearing, the low load bearing provides radial and outer axial support to remainder of rotor of electrical engine.

43. The aircraft set forth in claim 40 wherein said locking means on side of each said rotor have a locker comprising:

a drum, which fixed on setup flange of hollow shaft of electrical engine and used as rotational tier of said locking means;

a band brake, including band with frictional lining inside, correspondent to said drum and pivotally fixed by one end thereof on said electrical engine, and pulling lever, which pivotally connected to other end of said band by one end thereof, having a grove follower on other end thereof, and pivotally mounted on said electrical engine, the band brake used as irrotational tier of said locking means;

a main bracket fixed on said electrical engine;

an outer locking shaft, which has rotational support on said main bracket and used as handling tier of said locking means;

a screw, which fixed on said outer locking shaft in limits of said main bracket;

a conducting rod, which fixed on said main bracket, having axis thereof parallel to axis of said screw; and

a threaded lead, in which said screw screwed and which has an additional hole, which can move over said conducting rod, the threaded lead has an open grove in direction perpendicular of axis of said screw, in which said grove follower of pulling lever of band brake inserted, providing ability for precision control of said band brake.

44. The aircraft set forth in claim 43 wherein one side said locker selected as main, having outer locking shaft thereof connected to related tier of said handling means, and other side said locker selected as dependent, having outer shaft thereof connected to same of said main locker by gear means, using two pairs of meshed miter gears.

45. The aircraft set forth in claim 37 wherein a PGS gearbox placed for each said rotor near of floor of said fuselage, between said rotor'"'"'s socket and said force plate, comprising:

a body, which fixed to said force plate,

a set of three coupled shafts for all said PGS-components, which members have rotational support and oriented vertically;

a set of three primary shafts for all said PGS-components, which members have rotational support and oriented horizontally; and

a set of three pairs of meshed miter gears, which fixed on said respective coupled and primary shafts;

and wherein elements exist, accompanied to said PGS gearbox, comprising;

a set of three PGS couplings, which connect all outer shafts of said steering tier of setup of rotor with respective coupled shafts of PGS gearbox;

three windows in said rotor'"'"'s socket for all said outer shafts, in which said outer shafts can freely entered upon axial movement of said rotor in time of setup, and in which said PGS couplings can be rotated freely; and

three windows in said force plate, which placed against said respective socket'"'"'s-windows, these windows used for assisting in mounting of said PGS couplings upon setup of said rotor.

46. The aircraft set forth in claim 27 wherein pitch control of said stabilators has elements comprising:

a common pivot shaft, which connects said two side stabilators altogether;

a worm gear fixed on said common pivot shaft;

a worm bracket, which fixed on said fuselage by means ensuring fixed distance thereof from said common pivot shaft;

a steering shaft, which has rotational support in said worm bracket;

a worm fixed on said steering shaft and meshed with said worm gear;

a primary stabilator pitch shaft, which represents respective tier of said handling means; and

a universal joint, which connects said steering shaft with said primary stabilator pitch shaft.

47. The aircraft set forth in claim 29 wherein said airstream control system comprises:

a Stream Deviation Tube (SDT), placed on nose of said fuselage, which reflects deviation of airstream relative horizontal plane thereof to pair of pressures on respective pneumatic outputs thereof, where one of them outputs represents upward pressure, and other downward pressure; and

a pair of electrical sensors respectively connected to said pair of pneumatic outputs of said SDT, which convert respective pressures to electrical signals used as output of said airstream control system.

48. The aircraft set forth in claim 34 wherein a central computer can manage all tiers of said handling means.

49. The aircraft set forth in claim 34 wherein two racks placed inside of said fuselage near to respective electrical engines, these racks have said electrical sources fixed on shelves thereof and are movable along said fuselage by mechanical means as part of said handling means, including respective servos and encoders, for tune center of gravity of said aircraft dependently from load variation and for additional assisting to said stabilator controller.

50. The aircraft set forth in claim 48 wherein said airstream control system possess abilities to measure true aerodynamic speed (TAS) at least for said stream following feature, and said central computer can interpret handling commands, expressed in form of biangular values for respective rotors, to respective PGS-states, using said value of TAS and actual winding speed of said rotors from said engine controller.

51. The aircraft set forth in claim 38 wherein said electrical sources can receive and store electrical energy in any form, and energy supply means include power plant based on combustion engine with electricity generator installed inside of aft compartment of said fuselage, with related elements of interface thereof comprising:

a fairing with air inlet, which spanned between said both side rotor'"'"'s sockets over ceil of said fuselage, continues to aft and closes inside of interior thereof said air outlets of cooling systems of both electrical engines, so air from said cooling systems mixed with mainstream air of the air inlet;

an air-conducting envelope accepts air by its entry hole, placed inside of said fairing, directs it toward said combustion engine for cooling and breathing, and conducts exhaust of said combustion engine and hot air toward trailing edge of said fuselage, the air-conducting envelope wraps said combusting engine, generally having said electricity generator outside thereof, and has an air outlet on trailing edge of said fuselage; and

a power management circuit, which connected to said electricity generator, said electrical sources and to related tier of said handling means.

52. The aircraft set forth in claim 50 wherein said fuselage has a cabin with cockpit, which has handling elements comprising:

a display of said central computer;

a joystick connected to said central computer, which used as primary handler from side of pilot, providing commands based on variation of biangular values for respective rotors upon interpretation movements thereof by said central computer, presuming intuitive and pilot friendly intention of such movements;

a lock command button, which send command to said central computer for actuating said encoder of engine controller to position correspondent to zero target winding speed of said rotors;

a pair of buttons for increase-decrease target winding speed of said rotors by actuating said encoder of engine controller to respective directions; and

a versatile command pad from buttons, which used for customization handling of said aircraft and for management of said central computer;

and wherein said central computer can perform automatic lock of said rotors with zero target winding speed of rotors in case of magnitude of actual winding speed dropped below constrained threshold.

53. The aircraft set forth in claim 52 wherein said cockpit further has handling elements reflected in commands of said central computer comprising:

a handling control capturing button on said joystick, which used for enabling movements commands from said joystick with initial remembering absolute position of said joystick and biangular state of both rotors;

a pad of common handling for skew, opposite angle, biangular gain and main angle of both rotors simultaneously, having pair of increase-decrease buttons per each said handled parameter; and

a pad of in turn handling, which based on differential handling of biangular gain and on mixed handling of collective angle of said both rotors, the pad has buttons related to biangular gain in corners of quad thereof, and buttons related to collective angle on sides of quad thereof, here bottom corners buttons will decrease biangular gain for same side rotor with increasing on opposite side, and upper corners buttons perform opposite action, also here center side buttons will decrease collective angle for same side rotor with increasing on opposite side, and vertical center buttons act as complement for buttons of said pad of common handling on base of collective angles.

54. The aircraft set forth in claim 53 wherein said skew outer shaft of each said rotor used only for change skew, and wherein a set of trimmers rotationally connected to said respective servos and encoders of handling components for permitting manual handling of respective components by mechanical means in interior of each with high precision included, comprising:

two P-trimmers, which managed pitches of PGS-states of respective rotors, the each P-trimmer has a general scale with range from −

180°

to 180°

, which occupies full circle, and has tics distance on highest precision scale in order of 0.1′

;

two G-trimmers, which managed gains of PGS-states of respective rotors, the each G-trimmer operates over linear normalized gain, having a general scale with range from −

100% to 100%, and has tics distance on highest precision scale in order of 0.1%, also the G-trimmer has overall indication of gain or indication of pitch deviations in main and opposite points on skew direction;

two S-trimmers, which managed skews of PGS-states of respective rotors, the each S-trimmer has placement of scales thereof equal to placement to said P-trimmer;

a WST-trimmer, which manages target winding speed of said engine controller, the WST-trimmer has a positive segment of a general scale thereof about two times longer than negative segment, and has tics distance on highest precision scale no worse than 0.1 m/s in order thereof;

a SP-trimmer, which manages pitch of said stabilators, the SP-trimmer has a general scale with range about from −

30°

to 30°

, and has tics distance on highest precision scale in order of 0.1°

, also the SP-trimmer can indicate actual position of said stabilators by a pictogram of section of said stabilator; and

a L-trimmer, which manages locking state of said locking means, the L-trimmer has a general scale with range from about −

20% to 100%, where 0% reflects state when said irrotational tier of locking means touches said rotational tier of locking means, and full range thereof reflects full excursion of elements of said handling tier of locking means.

55. The aircraft set forth in claim 54 wherein said trimmers placed on said cockpit together with accompanied elements comprising:

a pair of increase-decrease buttons per each said trimmer, which used for changing value of respective component electromechanically by actuating respective servo, these buttons placed near respective trimmer (trimmer-buttons);

four locking knobs (L-knobs), which placed only near S-trimmers and G-trimmers as outer interface of their internal locking system and used for locking respective trimmers upon manual handling against possible mutually induced rotation of said outer shafts of rotors for skew and gain components, these locking knobs are handled by rotation between locking and non-locking position and have possibility of automatic unlocking for case of non-manual handling;

three pairs of increase-decrease buttons for changing pitch, gain and skew respectively and simultaneously for said both rotors electromechanically by actuating respective servos (common P-G-S-buttons);

a high speed button (HS-button) used for enabling high speed actuation for servos of pitch and skew, which action is applicable upon runway operations;

a pitch follows skew switch (S->

P-switch) used for enabling said P-trimmers follow with same speed and direction after respective changes of said S-trimmers upon pressing said common S-button, which action is applicable upon runway operations;

two sets of differential P-G-S-buttons, which placed apart on respective sides related to said rotors and will decrease pitch, gain or skew respectively for same side rotor with increasing on opposite side electromechanically by actuating respective servos;

a Stream Deviation Indicator (SDI) is a pneumatic indicator respectively connected to pneumatic outputs of said SDT and reflects pressure difference by position of arrow thereof, the SDI used upon manual handling of said SP-trimmer and for indication efficiency of the automatic controlled loop of said stabilator controller;

a WSA-indicator, which connected to said engine controller and reports actual winding speed of said rotors;

a RPM-indicator, which connected to said engine controller and reports actual RPM of said rotors;

a MR-indicator, which connected to said engine controller and reports actual external moment ratio on common central powering shaft of said rotors, which value is normalized to particular total weight of said aircraft;

a SF-switch, which used for enabling said “

Stream Following”

featured action of said stabilator controller;

a EC-switch, which used for managing power state of said engine controller; and

a CM-switch, which used for enabling computer management for said central computer over all trimmers.

56. The aircraft set forth in claim 55 wherein, said cockpit has an indicator panel, oriented generally vertically, which used for placement standard standby instruments of an airplane with following said elements of cockpit:

display, EC-switch, WSA-indicator, RPM-indicator and MR-indicator, and wherein said cockpit has also a control panel, sloped generally on 45 degrees and placed under said indicator panel as continuation thereof, having all said remained elements of said cockpit with placement, shaping and features comprising;

all elements of computer management placed in near under bottom of said display, having said pad of common handling on center of said display and of center from pilot;

said joystick placed on a pad, which hanged on a concave support from center of said control panel just below said pad of common handling;

said two sets of differential P-G-S-buttons placed on said control panel on respective sides from said concave support, having P-buttons thereof in inner-most position and G-buttons in outer-bottom position, and all these buttons have bottom arrowed shape for hint on decreasing nature thereof, where P- and G-buttons additionally have outward offset in shape of bottom-arrowed ends thereof for hint for turning impact thereof;

said common P-G-S-buttons and said HS-button placed on said pad of joystick from forward of said joystick, having P-buttons thereof on center of said pad and HS-button between pair of P- and S-buttons for hint on impact destination of said HS-button;

said S->

P-switch placed on rim of said pad of joystick near said pair of S-buttons for hint on accompanied control used with this activated S->

P-switch;

said two sets of P-G-S-trimmers placed on said control panel on respective sides from position of said display on corners of triangles, having P-trimmers in inner-bottom positions and G-trimmer in outer-middle positions for hint on maximal impact the last on turning operations;

said trimmer-buttons of P-G-S-trimmers placed generally in inner-bottom positions from respective trimmers, having different inclination from vertical with bottom-buttons on outside, which hint on different impact of respective components on turning operation and on side of normal turning, so trimmer-buttons for G-trimmers have maximal inclination and same buttons for S-trimmers are vertical;

said L-knobs placed generally in upper-outer positions from respective trimmers, minimizing effect of possible obstruction there from;

said WST-trimmer placed in upper-outer position on inner-most side of said control panel under WSA-indicator from said indicator panel, having trimmer-buttons thereof in upper-inner position;

said SP-trimmer placed under WST-trimmer, having trimmer-buttons thereof in bottom-inner position;

said SDI placed under said SP-trimmer, hinting on managing control thereof;

said SF-switch placed in upper-inner position from said SDI, hinting on enabling ability thereof in linking stabilator pitch managed by said stabilator controller with deviation remainder on SDI;

said L-trimmer placed on bottom of inner-most side of said control panel under G-trimmer, having trimmer-buttons thereof in upper-inner position; and

said CM-switch placed on top of inner-most side of said control panel over G-trimmer and oriented horizontal, having enabling articulation thereof pointed to said display for friendly hint on enabling state of computer management.

57. The aircraft set forth in claim 54 wherein, each set of said P-G-S-trimmers shared a common case with equilateral triangle placement for compactness.

58. The aircraft set forth in claim 52 wherein, said fuselage has vertical stabilizer with rudder, and said cockpit has two pedals for steering said rudder, connected with them by elements of respective tier of handling means.

59. The aircraft set forth in claim 38 wherein, said fuselage has two parking wheels, which rotationally mounted on two respective retractable parking support resided on lateral sides of said fuselage and occupies interior space near aft vicinity of said rotor'"'"'s sockets outside inner levels in axial direction of respective electrical engines, these parking support oriented and retracted generally in vertical direction, manufactured from lightweight alloy tube and each has accompanied features and elements comprising:

a slotted end has a slot for said parking wheel in center-plan of tubular end of said parking support and rounded with radius generally equal to half of cross-length thereof;

a axel for said parking wheel fixed on said slotted end, connecting sides thereof;

a conductor has shape of segment of tube, fixed on said fuselage and has inside interior thereof said parking support, providing transverse support thereto with possibility of vertical slipping;

a keying rib mounted along backward side of said parking support and enters in corresponding hole of said conductor, preventing rotation of said parking support;

a retracting screw aligned with axis of said parking support;

a threaded complement mounted inside of said parking support, wherein said retracting screw screwed inside thereof;

a heel fixed on upper side of fuselage and provides rotational support for said retracting screw;

a servo with gear means can rotate said retracting screw; and

a parking hatch placed on fuselage, can be opened outside upon pushing force of said parking wheel, can be retracting by using spring means and secured by electromechanical latch, having ability for pressurizing level of sealing.

60. The aircraft set forth in claim 35 wherein, active vibration reduction system (VRS) included for partially decreasing vibrations induced by remained variations of overall steering moment of said rotors over changing minor rotational phase thereof, comprising:

a minor phase sensor, which provides synchronization signal of minor phase of said rotors upon detecting occurring of crossing zero-phase point of said rotors by any wing thereof, including possibility perform this task by analyzing original current patterns from said power circuits in case of respective correlation exists;

a pattern store, which stores set of compensating patterns related to respective flight operations and respective load states, the pattern store connected to respective tier of said handling means for selecting any of stored pattern as an active pattern for use; and

a pattern generator, which connected to said minor phase sensor and said pattern store, and can play said active pattern, synchronized and scaled in time with said synchronization signal of minor phase from said minor phase sensor, the pattern generator passes output pattern signal thereof to said two power circuits for obtain desired level representation in currents of coils of said electrical engines.

61. A trimmer for high precision control and indication of bi-directional values of steering of a handled element over rotational transmission, comprising:

a case has generally cylindrical shape, closed from bottom only and has outside other end thereof fixtures for mounting said trimmer under corresponding hole of control panel of cockpit;

a primary shaft has rotational support in bottom of said case upon entering from outside and used to transmit rotational state to consumer of said trimmer or receive it back;

a primary rotated can mounted coaxially inside of said case with rotational support on bottom thereof, the primary rotated can has a handling ring around face side thereof;

a primary rotated scale with shape of ring, mounted coaxially inside of said handling ring of primary rotated can or can be integral part thereof, the primary rotated scale has tics and oriented to center thereof labels around ring thereof with highest precision, which service negative values of handled steering, and zero label thereof used as arrow for positive values, having an arrow like frame around there;

a handler mounted on said handling ring of primary rotated can, having face level thereof below face level of said case, and can be retracted up over level of said control panel, having rotational support in this retracted state, the handler used for manual handling of said trimmer by fingers;

at least one steady scale or shield with shape of ring, mounted coaxially on said case, having face level of each same as for said primary rotated scale, where inner most steady shield has a scale around outer perimeter thereof and a general scale around inner perimeter thereof, which exposes full range of values of said trimmer, and where each steady scale or said outer scale of shield services positive values of handled steering, and the scale for outer most case has same placement tics and horizontal oriented labels as for said primary rotated scale, being read against said arrow from primary rotated scale, and in other case an intermediate rotated scale presumed in outer neighborhood with similar placement rules as for said primary rotated scale, and zero value of said steady scale or outer scale of shield services as an arrow for said respective rotated scale for negative values of handled steering;

at least one rotated scale or shield with shape of ring or circle, mounted coaxially on said case with rotational support, having face level of each same as for said primary rotated scale, where any rotated scale services as said presumed respective intermediate rotated scale for negative values, and where outer most rotated shield placed inside of said inner most steady shield and pictures an arrow, which points to respective value on said general scale;

a set of gear means, where each member thereof used for transmitting rotation from said respective outer rotated scale or shield, including said primary rotated scale, to respective inner rotated next scale or shield with desired reducing, servicing all said rotated elements; and

primary stage gear means used for transmitting rotation of said primary rotated can to said primary shaft and vice versa.

62. A trimmer set forth in claim 61 wherein said steady and rotated scale or shields and respective set of gear means accommodated to intermediate level of indication upon including elements comprising:

a primary steady scale, placed inside of said primary rotated scale;

a intermediate rotated scale, placed inside of said primary steady scale;

a steady shield, placed inside of said intermediate rotated scale, having a intermediate steady scale around outer perimeter thereof;

a central rotated arrow shield placed inside of said steady shield;

a secondary stage gear means placed between said primary rotated can and said intermediate rotated scale; and

a tertiary stage gear means placed between said intermediate rotated scale and said central rotated arrow shield.

63. A trimmer set forth in claim 61 wherein, a functionality for mapping alternative values with low precision exists with features and elements comprising:

a window in said steady shield with thin arrow or line outside thereof for reading indication inside thereof; and

a mapping shield with shape of ring, coaxially clustered with said outer most rotated shield, having face level thereof below said steady shield and having an alternative scale around a sector thereof partially under said window of steady shield.

64. A trimmer set forth in claim 63 wherein, two windows for two variants of alternative values exist on said steady shield, instead of said one window, with different radial positions and non-overlapped angular segments thereof, and two alternative scales placed on said mapping shield respectively.

65. A trimmer set forth in claim 61 wherein said steady and rotated scale or shields and respective set of gear means accommodated to indication of actual position of a handled element upon including elements comprising:

a steady shield, placed inside of said primary rotated scale, having a primary steady scale around outer perimeter thereof;

a rotated arrow shield placed inside of said steady shield;

a central rotated shield of actual position placed inside of said rotated arrow shield, the central rotated shield of actual position has a pictogram of handled element, which angular position is equal to angular position of the handled element relative to a common base;

a secondary stage gear means placed between said primary rotated can and said rotated arrow shield; and

a tertiary stage gear means placed between said rotated arrow shield and said central rotated shield of actual position.

66. A trimmer set forth in claim 61 wherein said rotational support of said primary rotated can has elements and features comprising:

a central axel of case is integral part of said case and protrudes from said bottom thereof to interior thereof in coaxial position, the central axel of case has a threaded hole on axis thereof;

a spacer ring;

two bearings dressed over said central axel of case, separated by said spacer ring, dressed on said central axel of case too, the bottom bearing has axial support over inner ring thereof on said bottom of case, and the upper bearing has upper level thereof equal to upper level of said central axel of case;

a tail of primary rotated can is integral part of said primary rotated can as continuation from bottom thereof to down, the tail has a center hole with a small inner ring area inside, which separates outer rings of said two bearings inserted to this hole; and

a long central axel screwed to said threaded hole of central axel of case and has a flange, which laid on top of said central axel of case, providing axial support for inner ring of said upper bearing;

and wherein said primary stage gear means comprises;

a primary center gear fixed on said tail of primary rotated can; and

a primary pinion fixed on said primary shaft and meshed with said primary center gear.

67. A trimmer set forth in claim 61 wherein a rotated arrow shield placed inside of said steady shield with a secondary stage gear means placed between said primary rotated can and said rotated arrow shield, and all shields, inside of said primary rotated can, have support elements comprising:

a long central axel mounted coaxially on said case and protruded in interior of said primary rotated can, the axel has a threaded segment in middle thereof, a tail over the threaded segment and a threaded hole on axis thereof from top;

a primary steady can mounted coaxially on said threaded segment of long central axel between two nuts, which clamped a bottom thereof, the primary steady can has a thickened area on rim thereof, which used for mounting said steady shield;

a secondary rotated can mounted coaxially on said tail of long central axel with rotational support, the secondary rotated can has a thickened area on rim thereof, which used for mounting said central rotated arrow shield; and

a screw with washer fixed in said threaded hole of long center axel, providing upper axial support for said secondary rotated can;

and wherein said secondary stage gear means have elements comprising;

a flanged primary central pinion dressed over said long central axel and fixed on bottom of said primary rotated can, consuming own width flange for this fixation, the flanged primary central pinion isn'"'"'t touch said long central axel by central hole thereof;

a secondary shaft crossed bottom of said primary steady can with rotational support therein;

a secondary gear fixed on bottom end of said secondary shaft and meshed with said flanged primary central pinion;

a secondary pinion fixed on upper end of said secondary shaft; and

a secondary center gear mounted coaxially on bottom of said secondary rotated can and meshed with said secondary pinion.

68. A trimmer set forth in claim 67 wherein all gears of said secondary stage gear means manufactured from plastic, having features and elements comprising:

axial support of said secondary shaft provided by low friction hubs of said secondary gear and said secondary pinion;

radial support for said secondary rotated can provided by low friction central hole of said secondary center gear;

a low friction plastic washer placed between said upper nut and said secondary center gear for bottom axial support of said secondary rotated can, the plastic washer can be manufactured as integral part of said secondary center gear.

69. A trimmer set forth in claim 62 wherein said scales and shields, inside of said primary rotated can, have support elements comprising:

a long central axel mounted coaxially on said case and protruded in interior of said primary rotated can, the axel has a primary threaded segment in middle thereof, a tail over the primary threaded segment, a secondary threaded segment in middle of the tail, a short tile after the secondary threaded segment and a threaded hole on axis thereof from top;

a primary steady can mounted coaxially on said primary threaded segment of long central axel between two primary nuts, which clamped a bottom thereof, the primary steady can has a thickened area on rim thereof, which used for mounting said primary steady scale;

a secondary rotated can mounted coaxially on said tail of long central axel with rotational support, the secondary rotated can has a thickened area on rim thereof, which used for mounting said intermediate rotated scale;

a secondary steady can mounted coaxially on said secondary threaded segment of long central axel between two secondary nuts, which clamped a bottom thereof, the secondary steady can has a thickened area on rim thereof, which used for mounting said steady shield;

a rotated flange mounted coaxially on said short tail of long central axel with rotational support, the rotated flange used for mounting said rotated arrow shield; and

a screw with washer fixed in said threaded hole of long center axel, providing upper axial support for said rotated flange, these screw with washer placed inside of correspondent hole of said rotated flange;

and wherein said secondary and tertiary stages gear means have respective elements comprising;

a flanged primary central pinion dressed over said long central axel and fixed on bottom of said primary rotated can, consuming own width flange for this fixation, the flanged primary central pinion isn'"'"'t touch said long central axel by central hole thereof;

a secondary shaft crossed bottom of said primary steady can with rotational support therein;

a secondary gear fixed on bottom end of said secondary shaft and meshed with said flanged primary central pinion;

a secondary pinion fixed on upper end of said secondary shaft;

a cluster of secondary center gear and pinion mounted coaxially on bottom of said secondary rotated can, having pinion thereof inside of interior of said secondary rotated can, and center gear thereof meshed with said secondary pinion;

a tertiary shaft crossed bottom of said secondary steady can with rotational support therein;

a tertiary gear fixed on bottom end of said tertiary shaft and meshed with pinion element of said cluster of secondary center gear and pinion;

a tertiary pinion fixed on upper end of said tertiary shaft; and

a tertiary center gear mounted coaxially on bottom of said rotated flange and meshed with said tertiary pinion.

70. A trimmer set forth in claim 69 wherein all gears of said secondary and tertiary stages gear means manufactured from plastic, having features and elements comprising:

axial support of said secondary shaft provided by low friction hubs of said secondary gear and said secondary pinion;

radial support for said secondary rotated can provided by low friction central hole of said cluster of secondary center gear and pinion;

a low friction plastic washer placed between said upper primary nut and said cluster of secondary center gear and pinion for bottom axial support of said secondary rotated can, the plastic washer can be manufactured as integral part of said cluster of secondary center gear and pinion;

axial support of said tertiary shaft provided by low friction hubs of said tertiary gear and said tertiary pinion;

radial support for said rotated flange provided by low friction central hole of said tertiary center gear;

a low friction plastic washer placed between said upper secondary nut and said tertiary center gear for bottom axial support of said rotated flange, the plastic washer can be manufactured as integral part of said tertiary center gear.

71. A trimmer set forth in claim 61 wherein said primary rotated can has features and elements, related to sealing interior thereof, comprising:

a nest inside handling rim of said primary rotated can over face level of said primary rotated scale;

a rubber ring placed on bottom of said nest around periphery thereof;

a glass lid inserted in said nest and lays on said rubber ring; and

a glass retaining ring fixed on top of handling rim of said primary rotated can and retains said glass lid, the glass retaining ring has a hole correspondent to said handler.

72. A trimmer set forth in claim 61 were said handler and said primary rotated can have features and elements comprising:

a head exist on top of said handler with shape of ring of substantially increased diameter;

a hole exists in handling rim of said primary rotated can, therein said handler inserted from up and lays on said head with ability retracting by fingers;

a tail exist as continuation of said handler below bottom level of said handling rim;

a threaded hole exists on axis of said tail from bottom;

a tube dressed on said tail with possibility of free rotation thereon, the tube has outside diameter matched to diameter of said hole of handling rim for retaining against rotation and fall-down in retracted state of said handler by some friction; and

a screw with washer fixed in said threaded hole of tail, where outer diameter of the washer is substantially higher then diameter of said hole of handling rim, retaining said handler inside of trimmer and supporting said tube against fall-down.

73. A trimmer set forth in claim 61 wherein a locking system included with said trimmer, having a locking knob on said control panel, with features and elements of said system comprising:

locking needles equidistantly mounted on said primary rotated can or on continuation thereof, around perimeter thereof and outward from center thereof in non-obstructed area of said case;

a window exists on periphery of said case against area of said locking needles;

a locking bracket mounted on periphery of said case, having an interface of interior thereof with said window;

a solenoid mounted inside of said locking bracket with axis thereof directed toward said window;

a locking wedge, has magnetic tail inserted in said solenoid, the locking wedge can enter in said window with positioning between pair of neighbored locking needles, performing actual locking;

a spring dressed on tail of said locking edge, having back support on flange of said solenoid, the spring pushes said locking edge toward locking position thereof;

a rigid wire connected to end of tail of said locking wedge, going from a hole of mounting place of said solenoid in said locking bracket;

a soft string fixed to end of said rigid wire, the soft string can unlock said trimmer upon pulling other end of the string;

a pulley mounted on said locking bracket with possibility of free rotation, the pulley conduct said soft string to direction of said locking knob;

a bracket of locking knob mounted under said control panel near said trimmer;

a pulley of said locking knob mounted on said bracket of locking knob with possibility of free rotation, the pulley receive other end of said soft string from direction of said locking bracket;

a shaft of locking knob mounted inside of said bracket of locking knob with rotational support and has a tail protruded over face level of said control panel through correspondent hole thereon, the shaft has other end of said soft string fixed on middle segment thereof and can pull said soft string upon own rotation, having grove like envelope of clearance around of mating segment thereof with said soft string;

a shaft snapping system placed inside said bracket of locking knob and provides snapping with some force of said shaft in two angular positions related to locking and non-locking states of said locking knob; and

a handler of locking knob fixed on tail of said shaft and has a pointer, which indicates actual locking state of said locking knob.

74. A trimmer set forth in claim 61 wherein a servo mounted outside on bottom of said case, the servo provides rotation to said primary shaft and to consumer of said trimmer by using gear means mounted on bottom of said case.

75. A Stream Deviation Tube (SDT) for detecting deviation of airstream from plan of symmetry thereof in pitch direction generally and in form of two pressures, the SDT presumes use thereof by installation on forward of fuselage of an aircraft for detect deviation of said fuselage from stream following position, and the SDT comprising:

a consoling base, which used to positioning a forward end of said SDT on desired distance from said fuselage, the consoling base has generally tubular shape with conical narrowing to low diameter on forward end thereof;

a tubular case mounted on forward end of said consoling base and has outside diameter correspondent to said conical narrowing of consoling base;

a forward flange mounted on forward end of said tubular case and has outside diameter equal to outside diameter of said tubular case, the forward flange has symmetrical shape, looking from lateral direction, with two equal slopes on angle about 40 degrees from pitch plan symmetry thereof, having a entry channel on center of each said slope with continuation to respective output socket on mounting flange thereof;

two pressure output tubes, which mounted inside of said consoling base and provide upward and downward pressures to consumer; and

a system of pressure conduction, which conducts pressures from said output sockets of said forward flange to respective pressure output tubes.

76. A SDT set forth in claim 75 wherein said tubular case has transverse support upon inserting in correspondent hole in said conical narrowing of consoling base, and said system of pressure conduction and mechanical connectivity have features and elements comprising:

a collector has round flanged shape and mounted inside of said consoling base in rearward vicinity of said conical narrowing thereof, the collector has two said pressure output tubes brazed inside two respective holes thereof, and the collector has two other holes for fixing thereto other elements of said SDT;

a backward flange mounted inside of said consoling base in middle vicinity of said conical narrowing thereof, between said collector and said tubular case, inserting in said tubular case by a thin own centered area, the backward flange has two holes, which forward sides have entry sockets, and which backward sides have respective connectivity to said holes of collector for pressure output tubes, providing transition of pressure from short base between said entry sockets to increased base between said pressure output tubes, and also has two other holes, which coincide with said respective fixation holes of collector;

a centered area created on said forward flange, which inserted in forward end of said tubular case, providing transverse support for said forward flange;

two threaded holes exists on said centered area of said forward flange, correspondent to said two respective fixation holes of collector;

two tubes for upward pressure and backward pressure inserted in said respective output and entry sockets between said forward flange and said backward flange; and

two long bolts inserted from backward of said collector to said respective fixation holes in collector and backward flange, these bolts screwed in said respective threaded holes in forward flange, providing fixation for said forward flange, said tubular case, said backward flange and said two tubes for pressures.

77. A SDT set forth in claim 76 wherein said two bolts and said respective holes placed in vertical position, said output sockets of forward flange and said entry sockets of backward flange placed in horizontal position, each said of two tubes for pressures broken in two parts with a gap between them in middle, and a anti-icing and moisture eliminating system with features and elements included, comprising:

a moisture collector placed in said gap between said forward and backward pairs of pressure tubes, which entered in corresponding entry sockets thereof, the moisture collector has generally cylindrical shape with diameter equal to inner diameter of said tubular case with two mounting holes for said long bolts, and has two internal cavities in middle thereof symmetrically equal in lateral relation, which are opened to bottom and lateral directions, having separation by thick wall with said bottom mounting hole inside and by thin wall on bottom thereof, where moisture collected, and said cavities are connected by respective holes to said both sides entry sockets of said moisture collector;

a sealing lid has shape of segment of a tube, complementing perimeter of middle section of said moisture collector to completed circle, and seals said both cavities of said moisture collector by using a sealant, having a interface with said thin wall on bottom thereof, in which vicinity created two drain holes for said both respective cavities with symmetric placement;

two drain holes created on bottom of said tubular case, aligned in placement thereof with said two drain holes of sealing lid; and

two electrical heaters placed inside of said tubular case from each side of said moisture collector, having said forward and backward pressure tubes and said long bolts wrapped by tubular bodies thereof, these two heaters complemented with two electrical wires exited from said collector and have desired electrical connectivity between them and said two electrical wires by using correspondent holes created in said moisture collector, said backward flange and said collector for isolated electrical wires.

78. A SDT set forth in claim 77 wherein pressure connectivity in said forward flange and said backward flange have features and elements comprising:

two horizontal channels of forward flange, going from said respective output sockets inside of body of said forward flange on about middle of thickness of the body;

two diverting channels of forward flange drilled from cylindrical surface of said forward flange to interior thereof, laying in cross-section plan thereof and connecting said horizontal channels with respective entry channels, having inclination to horizontal plan about 45 degrees;

two seals of diverting channels seal outer-ends of said respective diverting channels from environment, repairing original cylindrical shape of said forward flange; and

two diverting channels of backward flange created on back side of said backward flange, have 90-degrees sectors for restore to original up-down position exit sites of pressure, providing vertical alignment for said two pressure output tubes with friendly direct geometrical relation between said two entry channels of forward flange and said two pressure output tubes.

79. A system of methods of operating and handling an aircraft, having two sets of wings placed apart of fuselage of said aircraft and involved in collective movement along a fixed loop relative to center plan of said aircraft with common and changeable winding speed of said wings along said loop with variable pitch steering of said wings for different phases along said loop, and where, for ground based reference frame, magnitude of variations of said pitch steering isn'"'"'t exceed 90 degrees, but collective steered pitch of said all wings can have any arbitrary value in range from −

180 degrees to 180 degrees, and where said aircraft accommodated by respective means for normal operations, keeping controlled pitch, with value of overall driving force, used for said collective movement of said wings, laid in range between 15 and 85 percents of entire weight of said aircraft generally, the system comprises methods of;

on runway acceleration, comprising steps of;

set distribution of pitches of said wings along said loop, having high angle of attack relative to sum of said winding speed, anticipated ground speed and anticipated inflow, related to anticipated thrust about 40 percents of entire weight of said aircraft, for phase of forward wings, at least moderate negative angle of attack for phase of backward wings, and intermediate pitches between these phase points;

establish high positive winding speed, where positive direction defined as having upper wings going to forward, and keep said distribution of pitches in accordance with changed ground speed, having acceleration about 0.3 g with desired margin; and

progressively decrease said positive winding speed upon increasing ground speed with correspondent change of said distribution of pitches with progressively increasing vertical component of thrust, having high acceleration and having consumed power near to maximal value designed for said aircraft;

flight handling, comprising steps of;

establish said fuselage in direction of flight path of said aircraft or with some other controlled angle in vicinity of ground case, and continue retain the state of said fuselage against changing pitch moment of said aircraft induced by said variable driving force, using said respective means;

set distribution of pitches of said wings along said loop generally in accordance with “

flying elevator”

conception and forward dominating wings i.e., having angles of attack inducing high load on loop'"'"'s segment tied to wings with high vertical moving component and placed more forward, and correspondingly having angles of attack inducing low load on loop'"'"'s segment tied to wings with high vertical moving component and placed more backward;

adjust distribution of pitches of said wings to desired horizontal acceleration of said aircraft induced by sum of gravitic propulsions of said all wings, gliding relative of respective local airstreams; and

adjust value and direction of said winding speed for having desired vertical movement of said aircraft, keeping said distribution of pitches of said wings for desired state of acceleration of said aircraft;

differentially adjust distribution of pitches of said wings between said two sets to control roll and yaw of said aircraft;

on runway deceleration, comprising steps of;

progressively increase collective pitch of all wings, keeping vertical component of thrust below entire weight of said aircraft, providing deceleration about 0.4 g with desired margin; and

maintain positive winding speed for having maximized deceleration after crossing of collective pitch of all wings value of 90 degrees and significantly dropped speed of said aircraft.

80. A system of methods as recited in claim 79 wherein said respective means for accommodating said aircraft to said variable driving force included two stabilators placed apart on aft of said fuselage of said aircraft, which used for compensation increasing from equilibrium pitch moment by increasing pitch thereon, and they used for compensation decreasing from equilibrium pitch moment by decreasing pitch thereon.

81. A system of methods as recited in claim 79 wherein said respective means for accommodating said aircraft to said variable driving force included means for moving parts of content of said fuselage, providing desired offset of center gravity of said aircraft, which used for compensation increasing from equilibrium pitch moment by shifting center gravity forward, and they used for compensation decreasing from equilibrium pitch moment by shifting center gravity backward.

82. A system of methods as recited in claim 79 wherein said loop has circular form by using two rotors with managed PGS-state and construed in accordance with four gears pitch steering scheme, and said variable ratio of driving force mapped to external moment ratio (EMR) with same range, and wherein common handling of said rotors for said on runway acceleration method comprises steps of:

set high negative gain about −

65 degrees;

set pitch and skew almost same and some below zero and stay use skew control for control pitch; and

progressively decrease magnitude of said negative gain upon increasing ground speed and decreasing said winding speed, and do it with simultaneously and progressively approaching said small negative values of skew and pitch toward zero for increasing vertical component of thrust;

and also wherein common handling of said rotors for said on runway deceleration method comprises steps of;

permit for rotors enter in deceleration of rotation thereof, but without dropping said winding speed below level about one third of specific stagnation speed of said aircraft, where said specific stagnation speed defined as speed, which stagnation on pitot-tube creates pressure equal to specific load of said wings of said rotors;

drop magnitude of high negative gain to moderate value about −

40 degrees;

set skew equal to current value of pitch and stay use skew control for control pitch with common value;

progressively increase skew and pitch up to value 90 degrees; and

increase skew and pitch up to value about 120 degrees for maximize remained deceleration after significant dropping of ground speed.

83. A system of methods as recited in claim 82 wherein said aircraft has a pitch-based biangular handling (P-mode) for said rotors of said aircraft, and wherein said P-mode biangular handling related to respective PGS-state by rules comprising:

handling skew in the handling mode is transparent to normal skew handling;

the handling consists from handling two formal pitch values placed apart on line of skew direction and belonged to idealized PGS-control, which has linear distribution of pitches between points laid on skew direction, and where value related to direction on skew referenced as main and other as opposite;

actual PGS-state mapped from set of selected skew and two biangular values by refactoring PGS-state for a pair of match-points, where the each match-point is some known value of entire pitch distribution exists in some known angular position in phase space;

the known angular positions of said match-points are simple two opposite directions on said line of skew shifted on some known phase shift;

the known values of said match-points are simple linear interpolations between said biangular values for respective known angular positions; and

the value of said known phase shift is product of some fixed empirical value and square root of normalized magnitude of gain with sign inverted to sign of gain, where maximal constructive limited value of gain used for said normalization.

84. A system of methods as recited in claim 83 wherein said fixed empirical value for said phase shift is about 24 degrees.

85. A system of methods as recited in claim 83 wherein said aircraft has an angle-of-attack-based biangular handling (A-mode) for said rotors of said aircraft, which used with conjunction with establishing of said fuselage in direction of flight path of said aircraft with some remained error, and wherein said angle of attack referenced as alpha, and said A-mode biangular handling related to respective PGS-state by rules comprising:

an error angle value considered and calculated as difference between orientation of said fuselage and direction of true airspeed (TAS) vector;

PGS-skew value equal to handling skew value minus said error angle value;

the handling consists from handling two formal alpha values placed apart on line of skew direction and belonged to idealized distribution of alphas, which has linear distribution of alphas between points laid on PGS-skew direction, and where value related to direction on skew referenced as main and other as opposite;

actual PGS-state mapped from set of corrected skew and two biangular values by refactoring PGS-state for a pair of match-points, where the each match-point is some known value of entire pitch distribution exists in some known angular position in phase space;

the known angular positions of said match-points calculated exactly by same rules as for said match-points of said P-mode of biangular handling; and

the known value of said each match-point is sum of related alpha from function of said linear distribution for known angular position of the match-point, with direction of TAS of a wing in the known angular position, where the TAS calculated as vectorial sum of tangential rotational component of the wing and TAS speed-vector of said entire aircraft, mapped to reference frame of said fuselage.

86. A system of methods as recited in claim 85 wherein common handling of said rotors for said flight handling method comprises steps of:

enable said A-mode of biangular handling;

ensure said main value of biangular handling higher then said opposite value of biangular handling;

set skew value near to zero;

adjust said main value of biangular handling to desired airspeed and horizontal acceleration, upon particular vertical speed;

adjust said opposite value of biangular handling to desired airspeed, performance and EMR;

adjust skew value for optimize performance, said EMR and flight path angle of said aircraft.

87. A system of methods as recited in claim 86 wherein differential handling of said rotors for said flight handling method for case of entering in turn upon A-mode of biangular handling has three categories including and comprising:

for ascending flight and cruise;

set a positive difference of out-turn relative in-turn main values of biangular handling of respective rotors, and set about half of it negative difference of out-turn relative in-turn opposite values of biangular handling of respective rotors;

for gliding with optimal speed;

set a positive difference of out-turn relative in-turn main values of biangular handling of respective rotors; and

for descending flight;

set a negative difference of out-turn relative in-turn main values of biangular handling of respective rotors, and set about same positive difference of out-turn relative in-turn opposite values of biangular handling of respective rotors, where the last value should be decreased in two times upon approaching to very high common main value of biangular handling.

88. A system of methods as recited in claim 86 wherein said flight handling method for case of high powering recuperative descent with high speed comprises steps of:

set skew about −

5 degrees for said both rotors;

progressively increase common main value of biangular handling to about 10 degrees higher then zero-lift alpha for airfoil used on said wings of rotors;

progressively decrease common opposite value of biangular handling to about 3 degrees higher then said zero-lift alpha upon said increasing of common main value; and

progressively and simultaneously with said changing of biangular values change said winding speed to high negative value about −

40 percents of said specific stagnation speed, having recuperating power about two thirds from maximal consuming power and flight-path angle about −

13 degrees in final state.

89. A system of methods as recited in claim 86 wherein said flight handling method for case of middle powering recuperative deceleration in descent with middle speed comprises steps of:

set skew about −

15 degrees for said both rotors;

progressively increase common main value of biangular handling to about 14 degrees higher then zero-lift alpha for airfoil used on said wings of rotors;

progressively decrease common opposite value of biangular handling to about 6 degrees higher then said zero-lift alpha upon said increasing of common main value; and

progressively and simultaneously with said changing of biangular values change said winding speed to high negative value about −

25 percents of said specific stagnation speed, having recuperating power about 40 percents from maximal consuming power, horizontal deceleration about 0.1 g and flight path angle about −

6 degrees in final state.

90. A computer memory based method for modeling flight an aircraft, having two sets of wings, belonged to two respective actuators placed apart of fuselage of said aircraft and involved in collective movement along a fixed loop relative to center plan of said aircraft with common and changeable winding speed of said wings along said loop with variable pitch steering of said wings for different phases along said loop, and where said actuators can be locked against moving said wings along said loop, and also said actuators considered by the method as one actuator with a common state, the method composed from operational tiers, memory state and processing, executed as sequence of cycles with some time-step on background of arbitrary handling and supervising, performing modification of said memory state for reflect actual modeling the flight in order of sequential rules of the method, doing calls to said tiers by demand of these rules, wherein said tiers used for modeling particular aspects of relation of said aircraft to flight for respective particular conditions comprising:

a tier of medium aspect, which used for modeling a medium enveloped said aircraft, particularly air and gravity acceleration, dependently from flying altitude;

a tier of wings placement aspect, which used for modeling distribution of position, speed directions and pitches for particular wings on said actuator, having relative reference frame placed in common origin of said actuators in center plan of said aircraft and oriented along ground and along said fuselage for said pitches only, the tier depends from said phase, from particular steering state of said actuators and from direction of said winding speed, where positive direction defined as having upper wings going to forward;

a tier of airfoil aspect, which provides access to respective datum of section coefficients and aggregations for broad range of Reynolds numbers and full 360 degrees range of angles of attack of airfoil used in said wings;

a tier of inflow aspect, which used for modeling end use inflow, dependently from thrust vector, overall true airspeed (TAS) vector, air density and outdated local airspeed (LAS) vector;

a tier of wings interference aspect, which used for modeling state of airspeeds for said all wings induced by vorticity distribution between said wings, dependently from provided state of cinematic viscosity, base flow LAS vectors, absolute pitches and origin referenced position of said wings, the tier provides end use state of LAS vectors;

a tier of a ground interaction aspect, which used for modeling a force induced from a undercarriage of said fuselage, dependently from position and speed of excursion of the undercarriage;

and wherein said sequential rules grouped in set of updates and queries, for friendly management and referencing over said rules, comprising;

a query altitude conditions for air density, cinematic viscosity and magnitude of gravity acceleration for aircraft position from said medium aspect tier;

an update predicted state comprising steps of;

updating predicted speed, location and winding speed of aircraft performed by numerical integration of respective current values on half of time-step, using an acceleration vector, the predicted speed vector and a winding acceleration of aircraft as respective derivatives; and

updating predicted speed and location of each wing performed by numerical integration of respective current values on half of time-step, using an acceleration vector and the predicted speed vector of the wing as respective derivatives;

an update airflow state comprising steps of;

updating magnitude of airspeed of aircraft from magnitude of respective predicted speed vector;

updating angle of attack of each wing as difference between pitch and LAS vector, where pitch provided from said tier of wings placement aspect with additional correction on a fuselage pitch angle, and LAS vector calculated as correction said current speed vector of the wing on an inflow vector;

simulating interference performs call to said tier of a wings interference aspect with providing all required information for it, restoring said absolute pitches from respective angles of attack; and

updating airflow state of each wing from result of interference simulation, including angle of attack, airspeed magnitude, Reynolds number, coefficients of lift, drag and moment and steering variation of angle of attack by steering stream by interference and inflow;

an update winding state comprising steps of;

checking locked state as a locking flag, and for case if it set and a target winding speed isn'"'"'t zero, going out from said updating winding state, and in other case resetting the locking flag and continue;

checking of predefined lockspeed threshold, and for case if an actual winding speed value below the threshold, setting said locking flag, setting a directed powering force to zero and going out from said updating winding state, and in other case continue;

obtaining a needed delta acceleration dependently from difference between said target winding speed and said actual winding speed and value of said winding acceleration, and with applying limitation based on reciprocated footprint of mass of all wings in total mass of aircraft; and

updating power force, by setting said directed powering force value to sum of an directed internal force with difference based on said calculated delta acceleration and mass of all wings, with applying a predefined maximal magnitude of the force for slipping over crossing thereof;

an update dynamic state comprising steps of;

updating fuselage drag force by building an aerodynamic force vector oriented against said predicted speed vector with magnitude based on a front area and a wet area of said fuselage, said magnitude of airspeed and said air density;

updating damper force, by building the damper force vector oriented generally in upper direction and with magnitude based on excursion of undercarriage under load of said aircraft and on predicted vertical speed of said aircraft, and obtained upon passing said two parameters to said tier of a ground interaction aspect;

updating gravity and total forces by building the gravity force vector with magnitude based on a glide mass of aircraft and said magnitude of gravity acceleration, and by building the preliminary total force vector from said vectors of aerodynamic, damper and gravity forces;

preparing intermediate accumulators for forces and moments, by assigning and resetting variables for accumulations aerodynamic forces, non-conservative forces, along-loop directed aerodynamic forces, external moments and internal moments from particular wings;

entering in walkthrough on all wings;

updating forces and pitch moment of current wing by building an aerodynamic force vector with drag footprint aligned in LAS direction based on predicted TAS angle and said steering variation of angle of attack, and with values of drag and lift derived from said respective coefficients, airspeed magnitude and wing'"'"'s area, by calculating the pitch moment from said respective coefficient of moment, airspeed magnitude, wing'"'"'s area and wing'"'"'s chord, by building a gravity force vector from values of a glide mass of wing and said magnitude of gravity acceleration, and by building a total force vector from said vectors of aerodynamic and gravity forces;

accumulating forces and moments of current wing by accumulating said aerodynamic force vector, by querying speed direction and position of current wing from said tier of wings placement aspect, by accumulating loop directed force obtained as scalar projection of said aerodynamic force vector on the speed direction, by accumulating external moment obtained as cross-product of the wing'"'"'s position with said total force vector, by accumulating said pitch moment on said internal moment accumulator, by rebuilding drag-only version of said aerodynamic force vector, and by accumulating the drag-only vector on said non-conservative forces accumulator;

exiting from said walkthrough on all wings;

totalizing forces by accumulating said preliminary aerodynamic force of aircraft to said non-conservative forces accumulator, and by accumulating said aerodynamic forces accumulator to said aerodynamic force vector and to said total force vector of aircraft;

updating thrust reporting by calculating a LAS vector from sum of said predicted airspeed vector and said inflow vector, by refactoring consumed thrust force from said loop directed forces accumulator, said actual winding speed and magnitude of the LAS vector, by normalizing the consumed thrust force on magnitude of said gravity force with obtaining a consumed thrust ratio (CTR) value, by calculating a true thrust force from said aerodynamic force vector upon subtracting vector in said non-conservative forces accumulator, by normalizing magnitude of the true thrust force on magnitude of said gravity force with obtaining a true thrust ratio (TR) value, and by obtaining a thrust angle (TA) as angle of said true thrust force;

updating directed internal force in case of set said locking flag by assigning inverted value of said loop directed aerodynamic forces accumulator to said directed internal force, and in other case the last acquired value of said directed powering force;

calculating components of total force per each wing by calculating a translation component as mass-proportional part of said entire total force vector, and by calculating an along-loop component as member-proportional part of sum of value of said loop directed aerodynamic forces accumulator with said directed internal force;

updating inflow by calling said tier of inflow aspect with passing thereto said air density value, said predicted speed vector, said LAS vector and said true thrust force vector;

entering in walkthrough on all wings;

correcting states for impact of current wing by querying speed direction and position of current wing from said tier of wings placement aspect, by calculating said total force of the wing as superposition of said translation component and projection of said along-loop component on said wing'"'"'s speed direction, and by discarding cross-product of said wing'"'"'s position with said total force from said external moments accumulator;

exiting from said walkthrough on all wings; and

totalizing moments by storing sum of values of said external moments accumulator and said internal moments accumulator as pitch moment of aircraft, and by storing said value of said internal moments accumulator as internal pitch moment of aircraft;

an update cinematic state comprising steps of;

updating states of a previous location and a previous kinetic energy from respective values of said current location and a kinetic energy of current state;

updating acceleration, location and speed by calculating said acceleration vector from ratio of value of said total force vector to value of said gliding mass, and by time-step integration of said location and current speed vectors over base cinematic equations;

calculating kinetic energy for fuselage by using said updated current speed and mass of fuselage;

entering in walkthrough on all wings;

updating previous location of current wing from said current location;

updating acceleration, location and speed of current wing by calculating acceleration vector from ratio of value of said total force vector to value of said gliding mass of wing, and by time-step integration of said location and current speed vectors over base cinematic equations;

calculating kinetic energy of current wing by using said updated current speed and said gliding mass;

exiting from said walkthrough on all wings; and

updating time of said processing by incrementing it on time-step;

an update power state comprising steps of;

checking locked state of said locking flag, and for case if it set ensuring locking is finalized by resetting values of said actual winding speed, said winding acceleration and a consumed power value with going out from said updating power state, and in other case continue;

calculating a power speed by building localized vector of changing position of any one wing upon subtracting localized previous position from localized current position, by querying speed direction of the wing from said tier of wings placement aspect, and by dividing projection of said localized vector on said speed direction on time-step;

updating winding acceleration, winding speed and consumed power by assigning to said winding acceleration result from dividing changing of said actual winding speed on time-step, by assigning said power speed to said actual winding speed, and by setting said consumed power to product of said directed powering force and said actual winding speed; and

updating gliding mass of aircraft, related to rate of consuming fuel, if it applicable;

an update actuator'"'"'s phase comprising steps of;

updating phase and checking its range by addition to current phase a ratio of product of said actual winding speed with time-step to length of said loop, and by normalizing this result in case of over-ranging; and

doing hard sync for each wing by querying speed direction and position of the wing from said tier of wings placement aspect, by setting to said current location superposition of said wing'"'"'s position and current location of entire aircraft, by setting to said current speed vector superposition of said wing'"'"'s speed direction scaled on said actual winding speed and current speed vector of entire aircraft, and by setting to said acceleration vector superposition of said wing'"'"'s speed direction scaled on said winding acceleration and acceleration vector of entire aircraft;

and an update report state comprising steps of;

calculating cruise power by calculating a gravitic power, using change of vertical component of said current location relative to same of previous location, by calculating a kinetic power, using change of said kinetic energy from said previous kinetic energy, by calculating an acceleration power, using change square of said current speed from square of said previous speed, by calculating an internal kinetic power as difference between said kinetic power and the acceleration power, by calculating an external consumer power as difference between said consumer power and said internal kinetic power, and by obtaining the cruise power as losses remained after subtraction said gravitic power and said acceleration power from said external consumed power;

updating cruise ratio by dividing said consumed power on said cruise power;

updating equivalent lift to drag ratio (LDR) and lift coefficient (CL) by calculating an average speed vector between said current speed vector and a previous speed vector, by calculating an equivalent drag as ratio of said cruise power to magnitude of the average speed, by calculating an equivalent lift as scalar projection of said aerodynamic force to direction orthogonal to said average speed, by obtaining the equivalent LDR as ratio of the equivalent lift and said equivalent drag, by calculating a stagnation pressure based on said average speed and said air density, and by obtaining the CL as ratio of said equivalent lift to product of the stagnation pressure and total area of wings;

updating previous speed vector from current speed vector;

updating winding ratio (WR), normalized acceleration and flight path angle (FPA) by calculating a LAS vector from said current speed vector and said inflow vector, by obtaining the WR as ratio of said actual winding speed to magnitude of the LAS, by obtaining the normalized acceleration vector from said acceleration vector and said gravity acceleration, and by obtaining the FPA as angle of said current speed vector; and

updating propulsion efficiency (PrE), power lifting speed (PLS) and true gliding lift to drag ratio (TGLDR) by calculating a propulsion inflow as scalar projection of said inflow vector on direction of said current speed vector, by obtaining the PrE as ratio of magnitude of said current speed vector and its sum with the propulsion inflow, by obtaining the PLS as ratio of said external consumed power, scaled on the PrE, to magnitude of said aerodynamic force, and by obtaining the TGLDR as ratio of said LDR to said PrE.

91. A method as recited in claim 90 wherein said update report state of said sequential rules further includes an obtaining of local glide angle of embedded virtual glider (LGA) comprising steps of:

preparing calculation of said LGA by obtaining a common direction of inertial vertical of said entire aircraft as normalized vector in inverted direction of said aerodynamic force, and by initializing an accumulating vector of LGA direction to zero value;

entering in walkthrough for all wings;

obtaining LAS vector of current wing by rotating said predicted speed vector of the wing to its said steering variation of angle of attack;

obtaining LAS direction vector of current wing as normalized vector of said LAS vector of the wing;

obtaining a weighting value for said LAS direction as inverted dot-product of said common direction on said aerodynamic force vector of current wing;

accumulating said LAS direction vector scaled on said weighting value to said accumulating vector of LGA direction;

exiting from said walkthrough for all wings; and

updating a LGA value as angle of said accumulating vector of LGA direction.

92. A method as recited in claim 90 wherein said tier of wings interference aspect uses set of general rules for modeling said interference upon entire processing thereof comprising:

said processing uses only one said actuator for considerations;

said processing has generally sequence of equal main cycles with number for said N wings on said actuator about 2N;

said processing considers cross-section of each wing of said actuator being split on M segments along chord of airfoil thereof, having known area and center for each said segment of said cross-section, where said center calculated as center of gravity of the segment;

said processing builds on said each main cycle a draft distribution of LAS vectors over said wings, by merging a draft distribution of modeled induced speed vectors with known base distribution of LAS vectors;

said processing sequentially accesses in each said main cycle each destination wing for calculate its own induced speed vector upon a destination cycle;

said processing sequentially accesses in said destination cycle each said segment of said wing for calculate its own induced speed vector upon a segment cycle;

said processing sequentially accesses in said segment cycle each other wing for calculating and accumulating a partial induced speed vector from the source wing upon a source cycle;

said processing considers for calculation said partial induced speed vector a vorticity source placed in some center of vorticity (CV) as approximation entire vorticity distribution around said source wing, dependently from angle of attack of said wing;

said processing considers for calculation said partial induced speed vector a vorticity destination placed on said center of segment;

said processing calculates said partial induced speed vector basically in accordance with Biot-Savart law, having signed magnitude equal to scalar projection of a circulation to direction of a z-axis, divided on length of circle with radius equal to length of radius-vector between said vorticity source to said vorticity destination and directed along cross-product of normalized vector on the z-axis and normalized vector on said radius-vector, having the z-axis oriented along any wing from said fuselage to outward, and having the circulation calculated in accordance with Joukowski theorem as cross-product of aerodynamic force vector of source wing on normalized vector of direction LAS of the wing and divided on air density, length of the wing and magnitude of the LAS;

said processing additionally corrects said partial induced speed vector by scaling on a 3-d factor coefficient, which calculated by subtracting from square root of sum one with square of a 3-d aspect coefficient at the 3-d aspect coefficient, where the 3-d aspect coefficient is ratio of said length of radius-vector between said vorticity source to said vorticity destination to length of wings;

said processing calculates said wing own induced speed vector upon a consolidation algorithm, which is a weighted average over all segments of the wing, having weighting coefficient equal to ratio of said area of current segment on sum of chord length with distance from said center of current segment to some focusing point on said airfoil or on vicinity thereof;

said processing uses center of aerodynamic force (CF) as said focusing point, dependently from angle of attack and Reynolds number of said wing, in form of pair of coordinates (CFx and CFy) relative leading edge of said airfoil;

said processing calculates for each main cycle respective angles of attack and Reynolds numbers for each wing and queries said tier of airfoil aspect for getting respective coefficients of lift and drag and said CFx and CFy as aggregations; and

said processing uses known pivot position of wings relative leading edge of said airfoil, pitches of respective wings and their positions as pivot coordinates for doing all desired transformation of position for all geometrical features used for said modeling.

93. A method as recited in claim 92 wherein said center of vorticity (CV) approximated by a empirical sequential rules comprising:

scale geometry of said airfoil for having chord length equal to one, if the length differed from one;

for given angle of attack (AoA) obtain magnitude of said angle of attack |AoA|;

assign a main angle of attack AoA′

with value of said AoA for case if the |AoA| isn'"'"'t higher than 90°

, and in other case assign the AoA′

to value of 180°

−

|AoA|;

calculate main x-component of said CV relative leading edge of said airfoil along its chord CVx′

as half of (1-sin(|AoA|)) in power 0.07;

assign x-component of said CV relative leading edge of said airfoil along its chord CVx equal to said CVx′

for case if the |AoA| isn'"'"'t higher than 90°

, and in other case assign the CVx to value of 1-CVx′

;

calculate y-component of said CV relative to chord of said airfoil in upper direction CVy as camber-line of said airfoil for said particular CVx; and

rescale CVx and CVy back to original scaling of said airfoil geometry, if it applicable.

94. A method as recited in claim 92 wherein said tier of wings interference aspect uses a particularly dimensionless scaling for simplify and speed up entire processing of said tier with definition rules comprising:

use said LAS vector in original form;

use a scaled chord length of said airfoil c′

equal to one instead original chord c;

use any geometrical one-dimension feature of entire process divided on length of original chord instead the original feature;

use any geometrical two-dimension feature of entire process divided on square of length of original chord instead the original feature;

use a scaled aerodynamic force vector AF′

instead said original aerodynamic force vector AF and defined as vector build on respective lift and drag coefficients in accordance to original transform relative to direction of said LAS of wing, and multiplied on half of square of said LAS; and

use a scaled circulation value instead said original circulation value and defined as cross-product of said scaled aerodynamic force vector AF′

with normalized vector along direction of the LAS, divided on magnitude of said LAS, using two-dimensional scalar version of said cross-product.

95. A method as recited in claim 94 wherein said entire processing of tier of wings interference aspect comprises from steps of:

enter in basic initialization;

acquire actual chord length of wings;

acquire said pivot position on said airfoil of wings scaled in said chord length;

acquire actual length of wings and scale it in said chord length;

do split said airfoil on said M segments and calculate area of each segment AS and center of each segment CSm as center of gravity;

acquire actual number of said wings N and establish storage of per wing states;

exit from said basic initialization;

receive call for demand of simulation and acquire cinematic viscosity, distribution of pivot positions, pitches and base LAS vectors over said wings;

normalize distribution of pivot position by scaling each position in said chord length;

calculate actual positions of centers of segments CSim per each wing dependently from respective position and pitch of the wing;

initialize resulted distribution of said LAS vectors by respective values of said base LAS vectors distribution;

enter in said main cycle of said processing, resetting a counter of main cycles;

enter in walkthrough over all wings;

calculate LAS magnitude and Reynolds number of current wing, using said cinematic viscosity and said actual chord length;

calculate angle of attack of current wing by subtracting respective LAS direction from pitch of the wing;

query said tier of airfoil aspect for respective coefficients and aggregations for current wing, passing to the tier said angle of attack and Reynolds number;

calculate said scaled aerodynamic force vector for current wing, using related lift and drag coefficients and said LAS vector;

calculate said scaled circulation value for current wing, using said scaled aerodynamic force vector and said LAS vector;

calculate said center of vorticity of current wing in airfoil'"'"'s reference frame, using said angle of attack of the wing;

calculate said actual position of said center of force of current wing by reposition center force coordinates from said obtained aggregations, using actual pivot position and pitch of the wing and said pivot position on said airfoil;

calculate said actual position of said center of vorticity of current wing by reposition said center of vorticity of current wing in airfoil'"'"'s reference frame, using actual pivot position and pitch of the wing and said pivot position on said airfoil;

exit from said walkthrough over all wings;

update said counter of main cycles and exit from said processing for case of reaching desired number of said main cycles, in other case continue;

enter in walkthrough over all destination wings;

enter in walkthrough over all segments of current destination wing;

reset value of induced speed vector of current segment of current destination wing;

enter in walkthrough over all source wings, excluding current destination wing;

calculate said radius-vector from said center of vorticity of current source wing to said center of current segment of current destination wing;

calculate direction of said partial induced speed vector from direction of said radius-vector;

calculate said 3-d aspect using magnitude of said radius-vector and said scaled length of wings;

calculate said 3-d factor, using said 3-d aspect;

calculate said signed magnitude of said partial induced speed vector, using said scaled circulation value of current source wing and magnitude of said radius-vector;

build said partial induced speed vector, using said signed magnitude, said 3-d factor and said direction thereof;

accumulate said partial induced speed vector on said induced speed vector of current segment of current destination wing;

exit from said walkthrough over source wings;

exit from said walkthrough over all segments of current destination wing;

calculate respective array of weighting coefficients for all segments of current destination wing, using respective distances of said centers of segments from said center of force of current destination wing and said respective areas of segments;

calculate consolidated induced speed vector of current destination wing from induced speed vectors of all segments of the wing, using said array of weighting coefficients;

accumulate said consolidated induced speed vector on said resulted LAS vector of current destination wing;

exit from said walkthrough over all destination wings; and

enter in next main cycle of said processing.

96. A method as recited in claim 90 wherein said loop has circular form by using two rotors with radius R from center axis of each said rotor to pivot axis of any wing thereof as said respective actuators, and wherein said tier of inflow aspect uses set of general rules for modeling said inflow upon entire processing thereof comprising:

said processing considers said inflow vector in result thereof oriented in opposite direction to said known true thrust;

said processing considers magnitude of said true thrust on other side equal to product of duplicated air density, a thrust specific area (TSA) of said aircraft, a magnitude of LAS vector and magnitude of said inflow vector, where said LAS vector should be equal to sum of said TAS vector and said inflow vector, implying a non-linear equation for resolving;

said processing uses Newton method (tangent method) for resolving said non-linear equation under low number of iterations;

said processing considers said TSA depends from a downwash specific area (DSA), propulsion specific area (PSA) and a thrust specific angle 13 between said true thrust vector and said LAS vector by a quadrature formulae implying said TSA equal to square root from sum o squares of DSA*sin(β

) and PSA*cos(β

);

said processing considers said DSA generally equal to area of circle with diameter based on total wingspan of said aircraft;

said processing considers said PSA generally equal to 4*L*R, where L is a common length of any wing of any said rotor; and

said processing uses said outdated known LAS vector for calculate said thrust specific angle β

.

97. A method as recited in claim 96 wherein each of said two rotors construed in accordance with four gears pitch steering scheme, having a central gear with omni-directional controlled offset from center of rotor, a one pitch gear per each said wing synchronized with the wing by angular position, and a one cluster per each said pitch gear, having a steering pinion meshed with said pitch gear and a entry gear meshed with said central gear, and wherein said tier of wings placement aspect uses managed PGS-state as said particular steering state, and uses set of general rules, for modeling distribution of pitches of particular wings upon entire processing thereof, comprising:

said processing considers axes of said pitch gears placed on a common circle around central axis of said rotor with radius R0;

said processing considers said pitch gear has radius r1, said center gear has radius r2, said entry gear has radius r3 and said steering pinion has radius r4;

said processing considers gear ratio of r1 to r4 equal to ratio of r2 to r3 and equal some constant K;

said processing considers a triangle build on axis of said pitch gear, axis of said central gear and axis of said cluster has two short sides with lengths r14=r1+r4 and r23=r2+r3 from sides of pitch gear and center gear respectively;

said processing considers a constant S1 equal to duplicated product of r14 and r23;

said processing considers a constant S2 equal to sum of squares of r14 and r23;

said processing considers, by using cosine theorem, a constant angle ω

0 equal to arccosine of ratio of difference of S2 and square of R0 to S1;

said processing considers distance between axis of said pitch gear and axis of said central gear as a variable r;

said processing considers, by using cosine theorem, a variable angle ω

1 equal to arccosine of ratio of difference of S2 and square of r to S1;

said processing considers a variable ω

=ω

1−

ω

0;

said processing considers a pitch deviation of said particular wing to which belongs said particular pitch gear, having particular r, as variable δ

=−

ω

*(1+1/K);

said processing considers angular direction from center of said rotor toward any particular wing is equal to same kind direction toward respective pitch gear of said wing, if other not specified;

said processing considers a direction of skew reflects skew-angle specified by S-component of said PGS-state in counter positive direction of said winding speed, beginning from forward-most position relative said fuselage;

said processing considers value of said r in said direction of skew has extremity with value r′

;

said processing considers a variable Δ

r equal to R0-r′

for case of normal assembling of said four gears pitch steering scheme, and considers equal to r′

-R0 for other case of inverted assembling, where inverted assembling defined as having said cluster in upper elongation, relative said pitch gear for zero-value direction of skew;

said processing considers a maximal magnitude of said Δ

r as a constant Δ

rmax;

said processing considers a difference between said pitch deviation in direction of skew and opposite direction as G-component or gain of said managed PGS-state and can pass it back by demand of this tier callers;

said processing considers an angular position of particular wing in counter positive direction of said winding speed, beginning from forward-most position relative said fuselage;

said processing considers a ratio of said Δ

r to said Δ

rmax as a linear normalized gain Gn and accompanied with said managed PGS-state for direct changing said gain; and

said processing considers said pitch of particular wing is equal to said pitch deviation 6 summed with P-component of said managed PGS-state.

98. A method as recited in claim 97 wherein said entire processing of said tier of wings placement aspect for case of querying pitch for given angular position comprises from steps of:

calculate a relative angular position by subtracting said S-component of said managed PGS-state from said given angular position;

build a vector of position of axis of said center gear, using said Gn accompanied said managed PGS-state, said Δ

rmax and skew;

invert sign of said vector of position of axis of said center gear for case is said inverted assembling specified;

build a vector of position of axis of said pitch gear, using said constant R0 and said given angular position;

build a distance vector by subtraction said vector of position of axis of said center gear from said vector of position of axis of said pitch gear;

obtain a distance as magnitude of said distance vector;

calculate said ω

1, using said distance and said constants of S1 and S2;

calculate said co, using said constant ω

0;

calculate said pitch deviation, using said ω

value and constant K;

invert sign of said pitch deviation for case is said inverted assembling specified; and

provide result as sum of said pitch deviation and said P-component of said managed PGS-state.

99. A method as recited in claim 96 wherein said updating speed and location of all wings step of update predicted state of sequential rules implements an advanced prediction updating comprising steps of:

calculating angular shift and centripetal acceleration by obtaining the angular shift upon dividing product of inverted half of time-step on said actual winding speed on said radius of rotor R, by obtaining a sign of centripetal acceleration as sign of said actual winding speed, and by obtaining magnitude of said centripetal acceleration as square said winding speed divided on said R;

entering in walkthrough of all wings;

obtaining current speed direction vector of current wing from said tier of wings placement aspect;

obtaining predicted speed direction vector of current wing by rotating said current speed direction vector on said angular shift;

obtaining current angular acceleration direction vector by rotating said current speed direction vector on product of 90 degrees with said sign of centripetal acceleration;

obtaining predicted angular acceleration direction vector by rotating said predicted speed direction vector on product of 90 degrees with said sign of centripetal acceleration;

obtaining predicted rotation impact acceleration vector by subtraction said current angular acceleration direction vector from said predicted angular acceleration direction vector with scaling on said magnitude of said centripetal acceleration;

updating a predicted acceleration vector of current wing by addition said predicted rotation impact acceleration vector to said acceleration vector of the wing;

updating said predicted speed vector of current wing by addition said predicted acceleration vector scaled on half of time-step to said current speed vector of the wing;

updating said predicted location vector of current wing by addition said predicted speed vector scaled on half of time-step to said current location vector of the wing;

exiting from said walkthrough of all wings.

100. A method as recited in claim 96 wherein said update dynamic state of said sequential rules further includes an updating on end thereof comprising steps of:

calculating a moment normalizing value by multiplying said gliding mass of said aircraft, said gravity acceleration and said radius of rotor R;

updating a moment ratio by dividing said pitch moment of aircraft on said moment normalizing value; and

updating an internal moment ratio by dividing said internal pitch moment of aircraft on said moment normalizing value.

101. A method as recited in claim 90 wherein said arbitrary handling provides for demand thereof a set of two handling angles of attack in two generally opposite and specified directions for reflect said kind of handling based on the set, namely biangular handling, in said modeling, and wherein a tier of handling interpretation included and provides mapping of said parameters of said biangular handling to particular steering state of said actuators, using said current speed vector of aircraft and said actual winding speed for match said two prescribed angles of attack upon call of said handling interpretation tier from a step placed on end of said update power state of sequential rules.

102. A system for cruise flight generally based on conception for performing powered flight of aircraft by performing work against gravity force, using gliding wing as steady support, namely “

flying elevator”

conception, comprising;

a fuselage, having generally streamlined elongated shape;

at least one laterally symmetrical wing or lightweight glider with control elements, having abilities for remote control of pitch, roll and yaw thereof in glide with payload hanged there under with generally width range of load force provided from said payload, the wing has mass generally on significant order less than said fuselage;

a wire per each said wing connected the wing with said fuselage, having a connection position to the wing on center chord thereof generally;

a wire winding system per each said wire, having the wire wound on a drum thereof and means for powering the drum for rotation with controlled winding speed in both directions, the wire winding system installed on said fuselage generally near of center gravity of said fuselage;

means for attitude control of said fuselage at least for pitch and yaw thereof for directing said fuselage in airstream direction, these means placed on said fuselage;

means for acquire remote control of each said wing installed on the wing in respective connectivity with said control elements;

means for remote control of each said wing from side of said fuselage, these means placed on said fuselage with respective connectivity with said means for acquire remote control of each said wing; and

a cruise control system with ability for manage at least said winding systems and said means for remote control of each said wing upon applying periodically and adaptive patterns of actuation said systems and means, generally in accordance with handling rules comprising;

any wing involved in winding-in movement relative to fuselage should have a pitch implying with true airspeed (TAS) vector thereof generally high load from side of wire thereof, if other handling rules don'"'"'t override it;

any wing involved in winding-out movement relative to fuselage should have a pitch implying with TAS vector thereof generally low load from side of wire thereof, if other handling rules don'"'"'t override it;

any winding system should switch direction of actuation thereof upon encountering respective limit of prescribed range of lengths of free wire outside of said respective drum, if other handling rules don'"'"'t override it;

any winding system should provide force on respective wire below prescribed operation limit;

any winding system should prevent forceless state of respective wire by respective winding-in actuation;

any winding system should operate in prescribed range of lengths of free wire outside of said respective drum, if other handling rules don'"'"'t override it;

any elongation of any said wing relative other said wing should reflect in a respective policy of proximity of said members of said elongation;

any elongation of any said wing relative fuselage should reflect in a respective policy of proximity of said members of said elongation;

any winding system shouldn'"'"'t imply force of respective wire for accelerate or decelerate respective wing outside prescribed limits of TAS of the wing;

overall force from all said wings and gravity force shouldn'"'"'t imply vertical and horizontal accelerations of said fuselage outside prescribed limits;

said system for cruise flight should have TAS magnitude of center gravity thereof between prescribed limits; and

said system for cruise flight should have TAS magnitude of center gravity near to desired handled value, if other handling rules don'"'"'t override it.

103. A system as recited in claim 102 wherein each said wing handling upon variation position of connection point thereon for said respective wire, and wherein said control elements reflected in a center node of the wing, which used simultaneously for connect said wire, having elements comprising:

two longitudinal pathways fixed on said wing along central chord of the wing on some equal distance from the chord each, having some window between them;

a caret mounted between said two longitudinal pathways and can be moved on said pathways in longitudinal direction;

two transverse pathways placed on forward and rearward sides of said caret or comprising said sides thereof, having some window between them;

two movable supports mounted on said two transverse pathways respectively and can be moved on said pathways in transverse direction;

a common frame pivotally fixed on said two movable supports, having common pivot axis thereof oriented in longitudinal direction and constraining fixed distance between said two movable supports;

a central shaft mounted between two sides of said common frame in transverse direction, having axis thereof crossed with said common pivot axis of said common frame;

a link pivotally mounted on said central shaft by upper end thereof inside said common frame;

a C-shape earring pivotally mounted on bottom end of said link and connected with end of said respective wire of said wing;

a transverse screw goes through a respective threaded hole in said one of two movable supports along said respective transverse pathway;

a transverse servo rotationally connected to said transverse screw and placed on one side of said caret;

a longitudinal screw goes through a threaded hole in respective element on side of said caret, along said respective longitudinal pathway; and

a longitudinal servo rotationally connected to said longitudinal screw and placed on said wing.

104. A system as recited in claim 103 wherein said system has two said wings, and wherein one of said two wings always placed over other said wing, having said wire thereof going freely through said central node of said other wing, using a pulley assembly inside of said common frame of said central node as substitution of said link for conduct said wire comprising:

two equal cheeks, where each has three holes in vertical direction with symmetrical placement relative of a central hole thereof, and said central hole used for pivotal connection thereof and said pulley assembly with said central shaft, having additional longitudinal offset for better securing of said wire of upper wing in direction opposite to direction of entering thereof to said pulley;

a upper shaft, which mounted between upper ends of said two cheeks;

a bottom shaft, which mounted between bottom ends of said two cheeks and used for mounting said C-shape earring;

three pulley respectively dressed on said upper, central and bottom shafts with possibility of free rotation, and having said wire of upper wing conducted between them with order based on known offset in longitudinal direction of said wire relative of other wire, so said wire of upper wing enters from bottom to said pulley assembly over the bottom pulley from direction of the known offset thereof, and also exits in same direction.

105. A system as recited in claim 102 wherein said system has one said wing, and wherein said fuselage includes two symmetrical wings mounted apart symmetrically with respective roll control and either with possibility of shared pitch control of said wing with fuselage or with possibility having independent said pitch control, and in any case said pitch control reflected in further handling rules of said cruise control system, referencing said one wing with wire as wired wing, comprising:

for case if said wired wing involved in winding-in movement relative to fuselage, said fuselage wings should have a pitch implying with TAS vector thereof generally low sustain support, if other handling rules don'"'"'t override it; and

for case if said wired wing involved in winding-out movement relative to fuselage, said fuselage wings should have a pitch implying with TAS vector thereof generally high sustain support, if other handling rules don'"'"'t override it.