Micro-rotorcraft surveillance system

• US 20050051667A1
• Filed: 12/19/2002
• Published: 03/10/2005
• Est. Priority Date: 12/21/2001
• Status: Abandoned Application

• Current Assignee: David J. Arlton, Paul E. Arlton
• Original Assignee: David J. Arlton, Paul E. Arlton
• Inventors: Arlton, David J., Arlton, Paul E.
• Application Number:
  US10/499,530
• Publication Number:
  US 20050051667A1
• Time in Patent Office: Days
• US Class Current: 244/17.110
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/028 Micro-sized aircraft
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/80 UAVs characterised by their small size, e.g. micro air vehicles [MAV]
• CPC Class Codes: B64U 20/10 for stealth, e.g. reduction of cross-section detectable by radars
• CPC Class Codes: B64U 20/40 Modular UAVs
• CPC Class Codes: B64U 2101/15 for conventional or electronic warfare
• CPC Class Codes: B64U 2101/20 for use as communications relays, e.g. high-altitude platforms
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/24 Coaxial rotors
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 40/20 for in-flight adjustment of the base configuration
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/20 Transmission of mechanical power to rotors or propellers
• CPC Class Codes: B64U 60/50 : with landing legs
• CPC Class Codes: B64U 60/60 : with rolling cages
• CPC Class Codes: B64U 70/20 : for releasing or capturing UAVs in flight by another aircraft
• CPC Class Codes: B64U 70/83 : using parachutes, balloons or the like
• CPC Class Codes: B64U 80/60 : by wearable objects, e.g. garments or helmets
• CPC Class Codes: B64U 80/70 : in containers B64U80/60 takes precedence
• CPC Class Codes: B64U 80/86 : Land vehicles
• CPC Class Codes: G08B 13/19619 : Details of casing
• CPC Class Codes: G08B 13/19621 : Portable camera
• CPC Class Codes: G08B 13/1963 : Arrangements allowing camera rotation to change view, e.g. pivoting camera, pan-tilt and zoom [PTZ]

Abstract

A flying micro-rotorcraft unit (18, 24, 310, 330, 370) is provided for remote tactical and operational missions. The unit (18, 24, 310, 330, 370) includes an elongated body (52) having an upper and a lower end. The body (52) defines a vertical axis (60). The unit (18, 24, 310, 330, 370) further includes a navigation module (54) including means for determining a global position of the elongated body (52) during flight of the unit (18, 24, 310, 330, 370). Rotor means of the unit (18, 24, 310, 330, 370) is coupled to the upper end of the elongated body (52) for generating a thrust force that acts in a direction parallel to the vertical axis (60) to lift the elongated body (52) into the air. The rotor means is located between the elongated body (52) and the navigation module (54).

Claims

1. A hand-held, miniature flying micro-rotorcraft unit comprising

a plurality of interchangeable, modular components coupled to one another to form a hand-held elongated body defining a vertical axis, and

rotor means coupled to an upper end of the hand-held elongated body for rotation about the vertical axis to lift the hand-held elongated body into the air, the rotor means being driven by drive means located within one of the interchangeable modular components of the hand-held elongated body.

2. The unit of claim 1, wherein the hand-held elongated body is generally cylindrical in shape and each modular component is also generally cylindrical in shape.

3. The unit of claim 1, wherein each modular component includes a first module coupler at a first end of the component, and a second module coupler at a second end of the component, and wherein the first module coupler of one of the modular components is adapted to be coupled to the second module coupler of another of the modular components.

4. The unit of claim 3, wherein the first module coupler includes a first toothed ring positioned to lie about the vertical axis and having outwardly extending teeth, and wherein the second module coupler includes a second toothed ring positioned to lie about the vertical axis and having inwardly extending teeth defining detents therebetween, the detents being adapted to receive the outwardly extending teeth of the first toothed ring.

5. The unit of claim 4, wherein each of the outwardly extending teeth of the first toothed ring include an outer end having an angled cam surface.

6. The unit of claim 1, wherein the plurality of modular components includes a navigation module comprising means for determining a global position of the hand-held elongated body during flight of the micro-rotorcraft unit, a rotor hub assembly of the rotor means, a drive module including the drive means, a power module including means for energizing the drive means, and a payload module comprising at least one of munitions, a biological sensor, a chemical sensor, a video camera, and an infrared camera.

7. The unit of claim 6, wherein the rotor hub assembly is coupled to and positioned between the navigation module and the drive module, and wherein the power module is coupled to the drive module, and the payload module is coupled to the power module so that the navigation module and the payload module are positioned to lie at opposite ends of the hand-held elongated body.

8. The unit of claim 6, wherein the payload module further includes autonomous autopilot means for controlling the directional stability, including yaw, pitch, and roll, of the of the hand-held, miniature, flying micro-rotorcraft unit during flight.

9. The unit of claim 1, wherein the rotor means includes a first hub, a plurality of rotor blades coupled to the hub, means for supporting the first hub for rotation about the vertical axis, and hinge means for coupling each rotor blade to the hub so that each rotor blade is movable between an extended position generally perpendicular to the vertical axis and a retracted position generally parallel to the vertical axis.

10. The unit of claim 9, wherein the hinge means includes spring means for normally biasing each rotor blade to the extended position.

11. The unit of claim 10, further including latch means coupled to the hand-held elongated body for maintaining each rotor blade in the retracted position against the bias of the spring means.

12. The unit of claim 1, further including landing means coupled to the hand-held elongated body for supporting the hand-held elongated body prior to flight and upon landing.

13. The unit of claim 12, wherein the landing means includes a plurality of landing legs each being pivotably coupled to the hand-held elongated body for movement between a landing position to support the hand-held elongated body in a generally upright position and a stowed position wherein each landing leg is generally parallel to the vertical axis of the hand-held elongated body.

14. The unit of claim 1, further including anti-torque means coupled to the hand-held elongated body for countering a torque generated by the rotor means to control rotation of the unit about the vertical axis.

15. The unit of claim 14, wherein the anti-torque means includes a first and second yaw control outrigger each including a boom having a first end coupled to the body and being positioned to lie generally perpendicular to the vertical axis, and rotor means coupled to a second end of the boom for rotation about an axis generally perpendicular to the boom and the vertical axis.

16. The unit of claim 14, wherein the anti-torque means includes a plurality of fins coupled to the band-held elongated body and positioned to extend away from the hand-held elongated body in a direction generally perpendicular to the vertical axis.

17. The unit of claim 1, further comprising telemetry uplink and downlink systems located within the hand-held elongated body and configured to receive information from a command center and configured to send information to the command center.

18. A hand-held, miniature, flying micro-rotorcraft unit comprising

a hand-held elongated body having an upper end and a lower end and defining a vertical axis,

a navigation module comprising means for determining a global position of the elongated body during flight of the micro-rotorcraft unit, and

rotor means coupled to the upper end of the hand-held elongated body and located between the hand-held elongated body and the navigation module for generating a thrust force that acts in a direction parallel to the vertical axis to lift the hand-held elongated body into the air.

19. The unit of claim 18, wherein the rotor means includes a pair of upper rotor blades coupled to a first rotatable hub, a pair of lower rotor blades coupled to a second rotatable hub, and means for supporting the first and second rotatable hubs for rotation about the vertical axis in opposite directions.

20. The unit of claim 19, wherein the second rotatable hub is positioned to lie between the hand-held elongated body and first rotatable hub and the navigation module is coupled to the first rotatable hub.

21. The unit of claim 19, wherein the rotor means further includes first means for rotating the first hub in a first rotational direction and for collectively and cyclically pitching the upper rotor blades as the upper rotor blades rotate in the first rotational direction and second means for rotating the second hub in an opposite second rotational direction and for collectively and cyclically pitching the lower rotor blades as the lower rotor blades rotate in the second rotational direction.

22. The unit of claim 19, wherein the rotor means further includes hinge means for coupling each of the upper rotor blades to the first rotatble hub and each of the lower rotor blades to the second rotatble hub so that each rotor blade is movable between an extended position generally perpendicular to the vertical axis and retracted position generally parallel to the vertical axis to permit the rotor blades to pivot so as to the steer micro-rotorcraft unit in flight in various directions to maneuver around various obstacles and over certain terrain.

23. The unit of claim 19, wherein the rotor means further includes hinge means for coupling each of the upper rotor blades to the first rotatable hub and each of the lower rotor blades to the second rotatable hub so that each rotor blade is movable between an extended position generally perpendicular to the vertical axis and a retracted position generally parallel to the vertical axis to permit the rotor blades to pivot so as to steer the micro-rotorcraft unit in flight in various directions to maneuver around various obstacles and over certain terrain.

24. The unit of claim 19, wherein the hand-held elongated body comprises a drive module comprising motor means for driving the rotor means to develop sufficient thrust to lift the hand-held elongated body into the air and to cause the upper and lower rotor blades to generate cyclic thrust forces to tilt the rotor means relative to the horizontal to cause the micro-rotorcraft unit to fly in a generally upwardly and horizontal flight direction.

25. The unit of claim 23, wherein the hand-held elongated body further includes a payload module comprising at least one of explosive or incendiary munitions and biological and chemical sensors.

26. The unit of claim 23, wherein the hand-held elongated body further includes a power module located between the payload module and the drive module and the power module provides means for energizing the motor means.

27. The unit of claim 19, wherein the rotor means further includes a planetary gear system located in each of the first and second rotatable hubs and each planetary gear system is configured to rotate the rotatable hub associated therewith about the vertical axis.

28. The unit of claim 27, wherein the hand-held elongated body comprises a drive module comprising motor means for operating the planetary gear systems to rotate the hubs and the upper and lower rotor blades about the vertical axis to develop sufficient thrust to lift the hand-held elongated body into the air.

29. The unit of claim 28, wherein the drive module and the rotor means cooperate to define means for forming a quick-disconnect module coupling between the drive module and rotor means.

30. A hand-held, miniature, flying micro-rotorcraft unit kit having component parts capable of being assembled at a micro-rotorcraft assembly site to provide a miniature flying surveillance machine operable by remote control, the kit comprising the combination of

a hand-held payload module including means for conducting surveillance activities during flight,

a hand-held lift generator module comprising a first hub supported for rotation about a vertical axis in a first direction to rotate a first pair of rotor blades coupled to the first hub, and a second hub supported for rotation about the vertical axis in a second direction to rotate a second pair of rotor blades coupled to the second hub,

a hand-held power module containing a supply of energy,

a hand-held drive module including means for rotating the first and second hubs in opposite directions about the vertical axis to turn the rotor blades to generate a thrust force that acts in a direction parallel to the vertical axis using energy stored in the hand-held power module, and

a quick-disconnect module coupling adapted to be installed at a junction between each pair of adjacent modules to retain each pair of adjacent modules in fixed relation to one another to unite the modules in series to cause the thrust force generated by the hand-held lift generator module to lift the united payload, power, and drive modules into the air to initiate flight.

31. The kit of claim 30, wherein the hand-held drive, power, and payload modules are united in series using quick-disconnect module couplings to produce a hand-held elongated body having an upper end and a lower end and the hand-held lift generator module is coupled to the upper end of the hand-held elongated body.

32. The kit of claim 31, wherein the hand-held elongated body is about 20 inches in length and about two inches in width.

33. The kit of claim 31, further comprising a hand-held navigation module comprising means for determining a global position of the hand-held elongated body during flight and wherein the hand-held navigation module is adapted to be coupled to the hand-held lift generator module using the quick-disconnect module coupling to position the hand-held lift generator module between the hand-held elongated body and the hand-held navigation module.

34. A co-axial rotorcraft capable of sustained horizontal flight comprising

an elongated body having an elongated body axis,

a first rotor blade connected to the elongated body and rotatable in a first rotation direction about a first rotor axis substantially parallel to the body axis,

a second rotor blade connected to the elongated body and rotatable in a second rotation direction about a second rotor axis substantially parallel to the body axis, the second rotation direction being opposite of the first rotation direction, and

the elongated body is supported in flight by the first and second rotor blades with the body axis in a generally vertical orientation.

35. The rotorcraft of claim 34 further having a body aspect ratio being greater than 2:

1.

36. The rotorcraft of claim 34 wherein the first rotor blade has a first root portion adjacent to the elongated body, a first tip portion spaced apart from the first root portion, a first blade axis extending between the first root portion and the first end portion, and the first rotor blade is foldable toward the body axis about a first folding axis perpendicular to the body axis to position the first blades axis in parallel relation to the body axis.

37. The rotorcraft of claim 34 wherein the elongated body further includes a first body module and a second body module, and the first and second body modules are connected with a quick-change module coupling.