Active maple seed flyer

• US 7,766,274 B1
• Filed: 03/13/2007
• Issued: 08/03/2010
• Est. Priority Date: 03/13/2006
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Allen, Edward H., Boesch, Brian P., Jameson, Stephen M.
• Primary Examiner(s): Mansen; Michael R
• Assistant Examiner(s): BENEDIK, JUSTIN M
• Application Number:
  US11/717,361
• Time in Patent Office: 1,239 Days
• Field of Search: 244/17.11, 244/17.25, 244/6, 244/7.A, 244/7.B, 244/7.C, 244/39, 244/173.1, 244/173.3, 244/137.1, 244/137.4
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/00 Rotorcraft; Rotors peculiar thereto
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/297 Tilting rotors

Abstract

An unmanned aerial vehicle (UAV) has a payload or body affixed at one end of an elongated airfoil. The entire airfoil/payload combination rotates about a center of mass to define a rotor disk. Thrust is provided by air-augmented rocket engine thrusting tangentially at a location remote from the payload. A control system maintains knowledge of its environment, as by a camera, to produce directional control signals which actuate lift control means in synchronism with the rotational position of the vehicle. A deployable object may be carried. Protection of the stowed vehicle is provided by blister packaging.

Claims

1. An apparatus for flight comprising:

an elongated airfoil portion having a tip end and a root end defined in longitudinal direction and a leading edge and a trailing edge defined in transverse direction;

a body portion rigidly affixed to the root end of the airfoil portion;

a propulsion means for generating a thrust jet of pressurized gas, the propulsion means provided within the body portion and the airfoil portion;

a thrust delivering orifice located near the tip end of the air foil portion for delivering the thrust jet of pressurized gas away from the leading edge and along a tangent to the tip end of the airfoil portion, wherein the apparatus'"'"' center of mass is located in the body portion whereby the thrust jet of pressurized gas causes the body portion and the airfoil portion of the apparatus to rotate together about the center of mass and enables the airfoil to generate lift for the apparatus; and

at least one upwardly-directed jet provided immediately adjacent to the trailing edge of the airfoil for delivering a flow of gas for adjusting the lift of the airfoil, wherein the flow of gas is a portion of the pressurized gas generated by the propulsion means that has been redirected to the at least one upwardly-directed jet.

2. The apparatus according to claim 1, further comprising at least one downwardly-directed jet provided immediately adjacent to the trailing edge of the air foil for delivering a flow of gas for further adjusting the lift of the airfoil, wherein the flow of gas is a portion of the pressurized gas generated by the propulsion means that has been redirected to the at least one upwardly-directed jet.

3. The apparatus according to claim 2, wherein the flow of gas delivered by the at least one downwardly-directed jet creates a separation bubble below the airfoil, thus, decreasing the lift.

4. The apparatus according to claim 1, wherein the propulsion means comprises an air-augmented solid-fuel rocket engine.

5. The apparatus according to claim 4, wherein the air-augmented solid-fuel rocket engine consumes solid fuel and comprises a first stage, a second stage and a third stage,

wherein in the first stage, the solid fuel is ignited an burned generating hot, high-pressure, fuel-rich gas that is exhausted from a nozzle into the second stage,

wherein the second stage comprises a supersonic ejector in which the hot, high-pressure, fuel-rich gas entrains additional air and establishes a normal shock wave across the throat of the supersonic ejector allowing the second stage to burn the hot, high-pressure, fuel-rich gas and passes a hot second stage exhaust having higher pressure to the third stage,

wherein the third stage comprises a subsonic thrust augmentation ejector that dilutes the hot second stage exhaust with air delivering the thrust jet of pressurized gas through the thrust delivering orifice.

6. The apparatus according to claim 1, wherein the flow of gas delivered by the at least one upwardly-directed jet creates a separation bubble above the airfoil, thus, increasing the lift.

7. The apparatus according to claim 1, wherein the rotating apparatus defines a rotor disk and the thrust jet of pressurized gas is directed generally in the plane of the rotor disk.

8. The apparatus according to claim 1, wherein the at least one upwardly-directed jet is provided generally between the tip end and the root end of the airfoil.

9. The apparatus according to claim 1, wherein the body portion is rigidly affixed to the root end of the airfoil portion such that the airfoil portion extend in one direction from the body portion.