Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft

• US 7,059,931 B2
• Filed: 05/26/2004
• Issued: 06/13/2006
• Est. Priority Date: 05/27/2003
• Status: Expired due to Fees

• Current Assignee: Veratech Aero-RPV Corporation
• Original Assignee: Veratech Aero-RPV Corporation
• Inventors: Dammar, Michael A.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US10/855,275
• Publication Number:
  US 20040251377A1
• Time in Patent Office: 748 Days
• Field of Search: 244/17.11, 244/23.B, 446/34, 446/36, 446/37, 446/38, 446/57, 446/58, 446/46, D12/326, D12/327
• US Class Current: 446/34
• CPC Class Codes: B64C 27/00 Rotorcraft; Rotors peculiar thereto
• CPC Class Codes: B64C 39/00 Aircraft not otherwise provided for
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/10 for stealth, e.g. reduction of cross-section detectable by radars
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/15 using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft'"'"'s single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft'"'"'s instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft'"'"'s attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft'"'"'s rotation cycle.

Claims

1. A rotorcraft capable of powered rotational flight, comprising:

one wing;

at least one thrust generator operatively connected to the wing; and

a center of mass that is located external to the rotorcraft, wherein the rotorcraft rotates about the center of mass.

2. The rotorcraft of claim 1, wherein the rotorcraft does not surround the center of mass.

3. The rotorcraft of claim 1, further comprising the at least one thrust generator defining a radial path, the at least one thrust generator being responsive to control signals for varying thrust at any selected position along the respective path to control the flight direction of the rotorcraft.

4. The rotorcraft of claim 1, further comprising the at least one thrust generator being a propeller.

5. The rotorcraft of claim 1, further comprising the at least one thrust generator being an impeller.

6. The rotorcraft of claim 1, further comprising the at least one thrust generator being a jet engine.

7. The rotorcraft of claim 1, further comprising the at least one thrust generator being a rocket.

8. The rotorcraft of claim 4, further comprising at least one electric motor, the motor drivingly connected to the at least one propeller.

9. The rotorcraft of claim 8, further comprising the at least one electric motor being driven with pulse width modulation.

10. The rotorcraft of claim 8, further comprising at least one battery, the battery providing power to the at least one electric motor.

11. The rotorcraft of claim 1, further comprising:

a longitudinal axis; and

at least two supports, the at least two supports being offset on either side of the longitudinal axis and operatively disposed between the wing and the at least one thrust generator.

12. The rotorcraft of claim 11 wherein the at least two supports are equally offset from the longitudinal axis.

13. The rotorcraft of claim 11, wherein the at least two supports are unequally offset from the longitudinal axis.

14. The rotorcraft of claim 1, further comprising at least two wings.

15. The rotorcraft of claim 11, further comprising a housing pod disposed between the wing and at least two supports.

16. The rotorcraft of claim 15, wherein the housing pod holds at least one component selected from the group consisting of:

flight control electronics, at least one electronic propeller motor, at least one battery, a digital camera capable of taking still photos or video, an infrared sensor, a global positioning sensor, a visible light sensor, an ultraviolet light sensor, a radio frequency sensor, an ultrasound sensor, a magnetic field sensor, and a chemical detection sensor.

17. The rotorcraft of claim 1, further comprising the rotorcraft being of unitary body construction.

18. The rotorcraft of claim 17, further comprising integrating at least one component into the unitary body constructed rotorcraft, selected from the group consisting of:

flight control electronics, at least one electronic propeller motor, at least one battery, a digital camera capable of taking still photos or video, an infrared sensor, a global positioning sensor, a visible light sensor, an ultraviolet light sensor, a radio frequency sensor, an ultrasound sensor, a magnetic field sensor, and a chemical detection sensor.

19. The rotorcraft of claim 1, further comprising the orientations of the at least one thrust generator being fixed.

20. The rotorcraft of claim 1, further comprising the orientations of the at least one thrust generator being changeable prior to flight.

21. The rotorcraft of claim 1, further comprising the orientations of the at least one thrust generator being changeable during flight.

22. The rotorcraft of claim 21, further comprising a remote control for changing the at least one thrust generator orientation during flight.

23. The rotorcraft of claim 1, further comprising control electronics and a remote control for controlling the altitude and direction of the rotorcraft during flight.

24. The rotorcraft of claim 16, further comprising a remote control for controlling the components during flight.

25. The rotorcraft of claim 18, further comprising a remote control for controlling the components during flight.

26. The rotorcraft of claim 1, further comprising at least one wheel disposed beneath the wing to aid in landing.

27. The rotorcraft of claim 1, further comprising a landing protrusion disposed beneath the wing to aid in landing.

28. The rotorcraft of claim 16, wherein the components further comprise a transmitter that provides automated flight path capability for the rotorcraft using the global positioning sensor.

29. The rotorcraft of claim 16, wherein the components further comprise:

a servo system to self-level the rotorcraft during flight; and

a sensor capable of detecting a thermal profile from the surrounding terrain.

30. The rotorcraft of claim 29 wherein the sensor comprises an infrared sensor.

31. The rotorcraft of claim 16, wherein the components further comprise a servo system to self-level the rotorcraft during flight, including an accelerometer capable of detecting whether the rotorcraft is level and providing the servo system with level detection data.

32. The rotorcraft of claim 11, further comprising the at least two supports being collapsible to allow flat storage and rapid unfolding and launch.

33. The rotorcraft of claim 17, further comprising a servo integrated in the unitary constructed body to dynamically control the attack angle of the wing.

34. The rotorcraft of claim 33, further comprising a remote control for controlling the attack angle of the wing.