Aircraft and missile forebody flow control device and method of controlling flow

Patent metadata

Field	Value
Publication number	US-10137979-B1
Application number	US-201113151640-A
Country	US
Kind code	B1
Filing date	Jun 2, 2011
Priority date	Jan 3, 2003
Publication date	Nov 27, 2018
Grant date	Nov 27, 2018

Abstract

A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.

First claim

What is claimed:

1. A method of stabilization and maneuvering a missile or aircraft comprising the steps of
a. estimating or determining side forces on a missile or an aircraft forebody based at least in part on a signal from at least one sensor; the missile or aircraft further comprising at least one deployable and retractable flow effector on the missile or aircraft forebody and a closed loop control system for controlling the at least one deployable and retractable flow effector at least in part by indirectly estimating or determining flow separation, or estimating or determining side forces on the forebody based on the signal from at least one sensor;
b. activating the at least one deployable and retractable flow effector to counteract or change the side forces by activation of the at least one deployable and retractable flow effector with the closed loop controller based on at least in part the signal of the at least one sensor;
c. re-estimating or determining side forces on the missile or aircraft forebody based at least in part on a signal from the at least one sensor; and
d. deactivating the at least one deployable and retractable flow effector by retracting the flow effector to a position at or beneath the surface of the missile or aircraft in response to reduced or changed side forces.

2. The method of stabilization or maneuvering in claim 1 , wherein the at least one flow effector is activated by deploying the at least one flow effector.

3. The method of stabilization or maneuvering in claim 1 , wherein the missile or aircraft forebody comprises at least six flow effectors wherein the at least six flow effectors are positioned and separated substantially equidistantly about a center of the forebody of the missile or aircraft, and the forebody is the front 25% of the length of the missile or aircraft.

4. The method of stabilization or maneuvering in claim 1 , wherein the forebody of the missile or aircraft is designed with asymmetries in the forebody.

5. The method of stabilization or maneuvering in claim 1 , wherein the at least one flow effector is activated at angles of attack of the missile or aircraft forebody of greater than about 20 degrees to counteract out-of-plane loading on the missile or aircraft caused by asymmetries on the forebody.

6. The method of stabilization or maneuvering in claim 1 , wherein the aircraft or missile further comprises an inertial measurement unit with an output, and the output of the inertial measurement unit is used to determine the missile or aircraft orientation with respect to a flow separation determined by the at least one sensor.

7. A method of stabilization or maneuvering a missile or aircraft comprising the steps of
a. estimating or determining side forces on a missile or an aircraft forebody based at least in part on a signal from at least one sensor; the missile or aircraft further comprising at least one flow effector on the missile or aircraft forebody, the forebody being the front 25% of the length of the missile or aircraft, and a closed loop control system for controlling the at least one flow effector at least in part by indirectly estimating or determining flow separation, or estimating or determining side forces on the missile forebody based the signal from at least one sensor;
b. activating the at least one flow effector to counteract or change the side forces by activation of the at least one flow effector with the closed loop controller based on at least in part the signal of the at least one sensor; and
c. re-estimating or determining side forces on the missile or aircraft forebody based at least in part on a signal from the at least one sensor.

8. The method of stabilization or maneuvering in claim 7 , wherein the at least one flow effector is positioned on the nose of the missile or aircraft.

9. The method of stabilization or maneuvering in claim 8 , wherein the at least one flow effector is deployable and retractable.

10. The method of stabilization or maneuvering in claim 9 , wherein the at least one flow effector is activated by deploying the at least one flow effector.

11. The method of stabilization or maneuvering in claim 7 , wherein the missile or aircraft forebody comprises at least six flow effectors wherein the at least six flow effectors are positioned and separated substantially equidistantly about a center of the forebody the missile or aircraft.

12. The method of stabilization or maneuvering in claim 7 , wherein the forebody of the missile is designed with asymmetries in the forebody.

13. The method of stabilization or maneuvering in claim 7 , wherein the least one flow effector is activated at angles of attack of the missile or aircraft forebody of greater than about 20 degrees to counteract out-of-plane loading on the missile or aircraft caused by asymmetries on the forebody.

14. The method of stabilization or maneuvering in claim 7 , wherein the aircraft or missile further comprises an inertial measurement unit with an output, and the output of the inertial measurement unit is used to determine the missile or aircraft orientation with respect to a flow separation determined by the at least one sensor.

15. A method of stabilization or maneuvering a missile or aircraft comprising the steps of
a. estimating or determining side forces on a missile or an aircraft forebody based at least in part on a signal from at least one sensor; the missile or aircraft further comprising at least one flow effector on the missile or aircraft forebody and a closed loop control system for controlling the at least one flow effector at least in part by indirectly estimating or determining flow separation, or estimating or determining side forces on the missile forebody based on the signal from at least one sensor;
b. activating the at least one flow effector to counteract or change the side forces by activation of the at least one flow effector with the closed loop controller based on at least in part the signal of the at least one sensor; and
re-estimating or determining side forces on the missile or aircraft forebody based at least in part on a signal from the at least one sensor;
wherein the at least one flow effector is activated at angles of attack of the missile or aircraft forebody of greater than about 20 degrees to counteract out-of-plane loading on the missile or aircraft caused by asymmetries on the forebody of the missile or aircraft.

16. The method of stabilization or maneuvering in claim 15 , wherein the at least one flow effector is deployable and retractable.

17. The method of stabilization or maneuvering in claim 15 , wherein the at least one flow effector is activated by deploying the at least one flow effector.

18. The method of stabilization or maneuvering in claim 15 , wherein the missile or aircraft forebody comprises at least six flow effectors wherein the at least six now effectors are positioned and separated substantially equidistantly about a center of the forebody of the missile or aircraft, and the forebody is the front 25% of the length of the missile or aircraft.

19. The method of stabilization or maneuvering in claim 15 , wherein the forebody of the missile or aircraft is designed asymmetries in the forebody.

20. The method of stabilization or maneuvering in claim 15 , wherein the aircraft or missile further comprises an inertial measurement unit with an output, and the output of the inertial measurement unit used to determine the missile or aircraft orientation with respect to a flow separation determined by the at least one

Assignees

• Prince Troy
• Lisy Frederick J
• Patel Mehul P
• Dicocco Jack M
• Carver Reed
• Schmidt Robert N
• Orbital Res Inc

Inventors

• Prince Troy
• Lisy Frederick J
• Patel Mehul P
• Dicocco Jack M
• Carver Reed
• Schmidt Robert N

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

• B64C5/12 Primary

  for retraction against or within fuselage or nacelle · CPC title

• F42B10/64

  of fins · CPC title

• B64C23/06

  by generating vortices · CPC title

• F41G7/00

  Direction control systems for self-propelled missiles (flight control B64C, G05D1/00 {; counter-measures against guided missiles F41H11/02; spin-stabilised missiles F42B10/26}; self-propelled or guided missiles having direction control systems only installed aboard F42B15/01; rocket torpedoes F42B17/00; marine torpedoes or sea-mines having self-propulsion means F42B19/00; locating by use of radio or other waves G01S; computing aspects G06) · CPC title