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

• US 7,104,862 B2
• Filed: 07/26/2005
• Issued: 09/12/2006
• 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:
  US11/189,605
• Publication Number:
  US 20050258304A1
• Time in Patent Office: 413 Days
• Field of Search: 244/17.11, 244/253.B, 446/34, 446/36, 446/37, 446/38, 446/57, 446/58, 446/46, D12/326, D12/327
• US Class Current: 446/36
• CPC Class Codes: B64C 27/00 Rotorcraft; Rotors peculiar thereto
• 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 method for increasing a rotorcraft'"'"'s stability during flight, comprising:

providing a rotorcraft with one wing, a longitudinal axis parallel to the wing, and at least one thrust generator operatively connected to the wing, wherein the at least one thrust generator is offset on either side of the longitudinal axis, the rotorcraft having a center of mass located external to the rotorcraft, and wherein the rotorcraft rotates about the center of mass; and

increasing the moment of inertia for the rotorcraft by increasing the offset of the at least one thrust generator from the longitudinal axis and from each other at least one thrust generator.

2. The method of claim 1, further comprising ensuring the rotorcraft body does not surround the center of mass of the rotorcraft.

3. A method of controlling the flight of a rotorcraft, comprising:

providing a rotorcraft with one wing and having a center of mass located external to the rotorcrafts structure, wherein the rotorcraft rotates about the center of mass;

providing at least one thrust generator operatively connected to the wing, wherein the at least one thrust generator defines a rotational path;

varying the thrust applied by the at least one thrust generator at any location along the rotational path of the at least one thrust generator to control the flight direction and altitude of the rotorcraft.

4. The method of claim 3, wherein the rotorcraft further comprises more than one wing.

5. The method of claim 3, further comprising remotely controlling the flight direction and altitude of the rotorcraft using a remote control device that transmits a control signal.

6. The method of claim 5, further comprising:

receiving the control signal;

processing the control signal using a radio receiver to generate information regarding the desired flight path and altitude;

generating a signal regarding information about the rotational phase of the rotorcraft at any given instant in time; and

processing the control signal and the current rotational phase of the rotorcraft to achieve the desired flight path and altitude.

7. The method of claim 5, further comprising providing an alternate control signal locating system in the event that contact is lost or disrupted between the remote control and the rotorcraft.

8. The method of claim 7, further comprising:

the locating system detecting a broadcast station signal; and

using the broadcast station signal to remotely control the rotorcraft.

9. The method of claim 6, further comprising:

providing a position sensor on the rotorcraft; and

using the position sensor to inform the rotorcraft of its location.

10. The method of claim 9, wherein the position sensor is a global positioning system (GPS) sensor, and further comprising:

automating the rotorcraft flight path by providing the rotorcraft with a series of GPS coordinates;

directing the rotorcraft to fly to the provided coordinates; and

remotely directing the rotorcraft to take and transmit photographic data at a given coordinate or drop a payload.

11. The method of claim 10, further comprising providing a self-leveling mechanism.

12. The method of claim 11, wherein the self-leveling mechanism is a servo system, and further comprising:

detecting level imbalances in the rotorcraft'"'"'s orientation using an infrared sensor to detect a thermal profile from surrounding terrain as the rotorcraft rotates; and

generating a servo signal to bring the rotorcraft to a level condition if an imbalance is detected.