Aircraft, missile, projectile or underwater vehicle with reconfigurable control surfaces and method of reconfiguring

Patent metadata

Field	Value
Publication number	US-9683820-B1
Application number	US-201313734368-A
Country	US
Kind code	B1
Filing date	Jan 4, 2013
Priority date	Dec 2, 2005
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

First claim

What is claimed:

1. A method of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle, or projectile comprising steps of:
causing an aircraft, missile, underwater vehicle, or projectile to move, take off, launch, or otherwise be released into a designed path of travel, the aircraft, missile, underwater vehicle, or projectile having a center of pressure and comprising a body, at least one control surface having an area, and a sensor or device for detecting changes in condition;
detecting with the sensor or device a change in condition requiring increased maneuverability or increased stability;
outputting from the sensor or device a signal indicating the change of condition detected; and
causing the area of the at least one control surface to be varied to increase maneuverability or increase stability by changing the center of pressure of the aircraft, missile, underwater vehicle or projectile based at least in part on the signal of the sensor or device,
wherein the sensor or device is a GPS, radar or an infra-red device.

2. The method of claim 1 wherein part of the at least one control surface is varied by exploding a releasable connector which connects the part of the at least one control surface to the rest of the control surface, releasing a clamp which holds the part of the at least one control surface to the rest of the control surface, removing a hinge which connects the part of the at least one control surface to the rest of the control surface, or exploding a bolt which connects the part of the at least one control surface to the rest of the control surface.

3. The method of claim 1 wherein the aircraft, missile, underwater vehicle or projectile comprises at least two control surfaces, wherein multiple removable control surfaces, when attached, form one control surface of the at least two control surfaces, and wherein the multiple removable control surfaces provide multiple states of stability.

4. The method of claim 1 where the sensor or device transmits a signal to a controller via a satellite.

5. A method of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle, or projectile comprising steps of:
causing an aircraft, missile, underwater vehicle, or projectile to move, take off, launch, or otherwise be released into a designed path of travel, the aircraft, missile, underwater vehicle, or projectile having a center of pressure comprising a body, at least one control surface having an area, at least one sensor or device for detecting changes in condition, the at least one sensor or device having a signal, and a closed-loop control system;
causing with the closed-loop control system the area of the at least one control surface to be varied based on the signal of the at least one sensor or device to increase maneuverability or increase stability by changing the center of pressure of the aircraft, missile, underwater vehicle or projectile,
wherein part or all of the at least one control surface is varied by exploding a releasable connector which connects the part of the at least one control surface to the rest of the control surface, releasing a clamp which holds the part of the at least one control surface to the rest of the control surface, removing a hinge which connects the part of the at least one control surface to the rest of the control surface, or exploding a bolt which connects the part of the at least one control surface to the rest of the control surface.

6. The method of claim 5 wherein the aircraft, missile, underwater vehicle, or projectile comprises at least two control surfaces used to change the center of pressure of the aircraft, missile, underwater vehicle or projectile.

7. A method of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle or projectile during travel comprising the steps of:
causing an aircraft, missile, underwater vehicle or projectile to move, take off, launch or otherwise be released into a designed path of travel, the aircraft, missile, underwater vehicle or projectile comprising a body, at least one control surface having an area, a sensor or device for detecting changes in condition, the sensor or device having a signal, and a closed-loop control system;
causing with the closed-loop control system the area of the at least one control surface to be removed or reduced during travel in response in part to the signal from the sensor or device to increase maneuverability or increase stability.

8. The method of claim 7 wherein the aircraft, missile, underwater vehicle, or projectile comprises at least two control surfaces.

9. The method of claim 7 wherein the sensor or device outputs the signal to the closed-loop control system which increases or decreases the area of the at least one control surface during travel based at least in part on the signal of the sensor or device.

10. The missile or projectile of claim 9 wherein the closed loop control system is a proportional-integral-derivative controller, an adaptive predictive controller or an adaptive predictive feedback controller.

11. The missile or projectile of claim 9 wherein the device or sensor is an infra-red sensor.

12. The missile or projectile of claim 9 wherein the device or sensor is a radar.

13. The missile or projectile of claim 9 wherein the device or sensor is a GPS device.

Assignees

• Orbital Res Inc

Inventors

• Patel Mehul
• Ng T Terry
• Cain Alan B
• Sowle Zak
• Dicocco Jack

Classifications

• F42B15/01

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title

• F42B10/02

  Stabilising arrangements · CPC title

• F41G7/20

  based on continuous observation of target position · CPC title

• F42B10/64 Primary

  of fins · CPC title

• F42B15/00

  Self-propelled projectiles or missiles, e.g. rockets; Guided missiles (F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K) · CPC title