NOVEL HELICOPTER

• US 20090032638A1
• Filed: 10/06/2008
• Published: 02/05/2009
• Est. Priority Date: 04/07/2006
• Status: Active Grant

• Current Assignee: Ou Zhao, Qin Zhao
• Original Assignee: Ou Zhao, Qin Zhao
• Inventors: ZHAO, Qin, ZHAO, Ou
• Granted Patent: US 7,871,032 B2
• Time in Patent Office: Days
• US Class Current: 244/6
• CPC Class Codes: B64C 27/16 Drive of rotors by means, e.g. propellers, mounted on rotor blades
• CPC Class Codes: B64C 27/18 the means being jet-reaction apparatus
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings

Abstract

This invention discloses a helicopter that can directly propel rotors into the hovering state with drive, comprising a fuselage (13), a rotor (5) with a pull rod and jackstay (2), a turbine (1), a pair of wings (14), a hollow short shaft (37), a hollow short dead axle (36) with a bearing and a base (7), a plurality of throttle lines (35), a plurality of wires (34), a fuel delivery pipe (30), a hydraulic system, a axle sleeve (4) and a root axle (3), wherein the centrifugal-force-resistant turbine (1) directly drives the two-symmetrical-blade rotor (5), the turbine (1) is installed on the hollow short shaft (37), the hollow short shaft (37) is installed inside the hollow short dead axle (36), the hollow short dead axle (36) is fixed beside a root of the rotor (5), the hydraulic system controls a propelling direction of the turbine, the throttle lines (35), the wires (34) and the fuel delivery pipe (30) pass through the hollow short shaft (37) and are received in a crossbeam of the rotor, the axle sleeve (4) of the rotor is installed on the hollow dead axle (36), and hinged with the root axle (3) and the pull rod and jackstay (2), the base (7) is fixed on the back of a gravity center of the fuselage (13), pipelines are led to a underneath of the base and connected with a control system, and steering, outward pushing, positioning and propelling control is provided by a drive under the wings (14) or the fuselage (13).

Claims

1. A helicopter that can directly propel rotors into the hovering state with drive, comprising:

a fuselage (13);

a rotor (5) with a pull rod and jackstay (2);

a turbine (1);

a pair of wings (14);

a hollow short shaft (37);

a hollow short dead axle (36) with a bearing and a base (7);

a plurality of throttle lines (35);

a plurality of wires (34);

a fuel delivery pipe (30);

a hydraulic system;

a axle sleeve (4); and

a root axle (3);

wherein

the centrifugal-force-resistant turbine (1) directly drives the two-symmetrical-blade rotor (5);

the turbine (1) is installed on the hollow short shaft (37);

the hollow short shaft (37) is installed inside the hollow short dead axle (36);

the hollow short dead axle (36) is fixed beside a root of the rotor (5);

the hydraulic system controls a propelling direction of the turbine;

the throttle lines (35), the wires (34) and the fuel delivery pipe (30) pass through the hollow short shaft (37) and are received in a crossbeam of the rotor;

the axle sleeve (4) of the rotor is installed on the hollow dead axle (36), and hinged with the root axle (3) and the pull rod and jackstay (2);

the base (7) is fixed on the back of a gravity center of the fuselage (13);

pipelines are led to a underneath of the base and connected with a control system; and

steering, outward pushing, positioning and propelling control is provided by a drive under the wings (14) or the fuselage (13).

2. The helicopter of claim 1, wherein

the root axle (3) is concentric with an inner axle of a crossbeam of the rotor and hinged with the axle sleeve (4);

one end of the pull rod and jackstay (2) is hinged with an axle in the crossbeam of the rotor, and the other side thereof is hinged with a lower part of the pull rod and jackstay (2) and installed on the base (7).

3. The helicopter of claim 2, wherein

a pitch-changing lock of rotor (11) is disposed on sections of sliding keys at the bottom of the axle sleeve (4);

a locking embedded key (9) is disposed in the bottom of the axle sleeve (4);

a key slot segment (12) with increased diameter that is corresponding to the locking embedded key (9) is installed on the base (7), and locked up by a control system of the plectrum plate;

slip rings and chute systems are disposed on the external cylindrical sections of the pitch-changing lock of rotor (11);

the pitch-changing that can slide up and down is controlled by the control system of shifting fork or clamping-type shifting fork.

4. The helicopter of claim 1, wherein

the turbine (1) is fixed by a short shaft system;

the turbine (1) on the sides of the rotor roots steers by a hydraulic system and is of functions of adjusting and impelling directions of the helicopter;

the connection and control principle is the same as the following principle;

under parts between the two rotors (5) are the base of the hollow dead axle (7), and a rotary fuel delivery pipe (15), a protection pipe (10) are also passed through which to be interlinked with the axle sleeve (4);

throttle wires, wires and the turbine (1) shall steer to the pulling wire of hydraulic valve or gas mixture pipe of the internal-combustion engine (1), throttle wire and etc shall be led to the underneath of the base;

uncover the protection pipe (10) with key slot segment (12);

wires are connected to a slip ring, and are conducted by a clamping-type shifting fork control or a pressure carbon brush;

the rotary fuel delivery pipe (15) is connected with connector of rotary fuel delivery pipe (6);

if the rotary fuel delivery pipe (15) is a rotary pipe of mixture gas, the carburetor is equipped therebelow to realize fuel transportation and functional control.

5. The helicopter of claim 4, wherein

steering of turbine (1) on the rotors or pitch-changing of propellers is driven by pressure of the fuel delivery pump and controlled by a hydraulic valve;

the hydraulic tank is driven by pressure of the fuel delivery pump so as to enable the centrifugal-force-resistant propeller-fan or fan turbine (1) to control the propelling direction while the rotor (5) changes into a hovering state and to realize the pitch changing of propellers.

6. The helicopter of claim 5, wherein

the turbines (16) on both sides of the wings shield the rotor (5) purling via surfaces of the wings (14);

the turbines (16) on both sides of the wings are staggered with air stream on a surface of the drive (1) of the rotor (5).

7. The helicopter of claim 6, wherein the air stream on the wings (14) or fuselage drive (16) blows over the horizontal empennage and provides propelling or anti-propelling, steering and positioning so as to realize posture control and flying while rotors change into the hovering state.

8. A helicopter directly propelling rotors into a hovering state with drive, comprising:

a fuselage (13);

a two-symmetrical-blade rotor (5);

a pair of wings (14);

a propel with clockwise (CW) and counterclockwise (CCW) rotation functions;

a two-stroke low-emission internal combustion engine;

a plurality of throttle wires (35);

a plurality of wires (34);

a curling fuel delivery pipe (30);

a root axle (3);

a axle sleeve (4);

a hollow dead axle (21) with a bearing; and

a base (7);

wherein

the propel with CW and CCW rotation function and the two-stroke low-emission internal combustion engine are directly fixed beside the root of the rotor (5) directly drive the two-symmetrical-blade rotor (5);

the throttle wires (35), the wires (34) and the curling fuel delivery pipe (30) pass through a crossbeam and are received in the root axle (3) of the rotor;

the axle sleeve (4) is installed on the hollow dead axle (21) and hinged with the root axle (3);

the base (7) is fixed on the back of a gravity center of the fuselage (13);

pipelines are led to a underneath of the base and connected with a control system;

steering, positioning and propelling control are provided by a drive under the wings (14) or the fuselage (13).

9. The helicopter of claim 8, wherein

the internal combustion engine provides lean combustion for the stratification of two-stroke;

a pair of one-way air valves (17) are disposed on a scavenging port (43) and an air passages (20) on both sides;

a check valve of gas mixture (18) is disposed at the center of a long mid-way air passages (19) and in the vicinity of the one-way air valve (17);

each air throttle of the one-way air valve (17) is coupled synchronously with that of the check valve of gas mixture (18) so as to shield a gas mixture with the air in a cylinder; and

an air filter is installed outside of the unidirectional air valve.

10. The helicopter of claim 9, wherein the leaked or residual fuel is directly transmitted to the inlet of air compressor or interval sections in front of the air compressor and the combustor after injection, so as to make it burned in the internal combustion engine along with the air.

11. The helicopter of claim 9, wherein the fuel is directly injected into the cylinder of internal combustion engine;

and small amount of fuel that leaked from coupled parts of the nozzle is led to a scavenging duct through the oil pipe.

12. The helicopter of claim 8, wherein the fuel is directly injected into the cylinder of internal combustion engine;

and small amount of fuel that leaked from coupled parts of the nozzle is led to a scavenging duct through the oil pipe.

13. The helicopter of claim 8, wherein a stub wing (44) is fixed on a rotor head (47) directly.

14. A helicopter capable of propelling rotors directly, comprising:

a centrifugal-force-resistant turbine or an internal combustion engine (1);

a rotor (5);

a pair of symmetric stub wings (44);

a rotor head (47);

a automatic tripper (46); and

a pitch-changing connecting rod (45);

wherein

the centrifugal-force-resistant turbine or the internal combustion engine (1) is fixed on the rotor (5) or the symmetric stub wings;

the stub wings (44) are fixed on the rotor head (47) so as to enable the rotor (5), the automatic tripper (46) and the pitch-changing connecting rod (45) there between to operate altogether.

15. The helicopter of claim 14, wherein a stub wing (44) is wrapped outside a root axle extending from the rotor (5), so that transmission of the automatic tripper (46) is transmitted to the rotor root axle (3) via the pitch-changing connecting rod (45).

16. The helicopter of claim 14, wherein a stub wing (44) is supported by one end of the pull rod and jackstay (2), and the other end thereof is connected with an axle sleeve below the rotor head (47).

17. The helicopter of claim 14, wherein the propeller equipped centrifugal-force-resistant internal combustion engine (1) is fixed on the side of the root axle (3) and hinged on the root axle (3) via one end of the pull rod and jackstay, and the other end thereof is hinged with the axle sleeve rotating along with the rotor (5).

18. The helicopter of claim 17, wherein a hanging seat (49) in the cabin of the super-light helicopter (51) is disposed below the hollow dead axle (21) to realize accurate positioning in the air by transferring center of gravity through strength of hands and feet of the driver and passengers.

19. The helicopter of claim 18, wherein the propeller equipped centrifugal-force-resistant internal combustion engine (1) is fixed on the side of the root axle (3) directly;

and a working angle of the rotor (5) shall be controlled by a pitch-changing device so as to realize pneumatic control.

20. The helicopter of claim 19, wherein a controllable positioning pin (53) is installed below a entirely rigid hanging seat (49);

and is locked to a floor pin hole (48) of the super-light helicopter (51) after VTOL.