Hierarchical closed-loop control system for aircraft, missiles and munitions

• US 8,548,650 B1
• Filed: 04/25/2012
• Issued: 10/01/2013
• Est. Priority Date: 01/03/2003
• Status: Expired due to Fees

• Current Assignee: Orbital Research, Inc.
• Original Assignee: Orbital Research, Inc.
• Inventors: Prince, Troy S., Kolacinski, Richard, Patel, Mehul
• Primary Examiner(s): BEHNCKE, CHRISTINE M
• Application Number:
  US13/455,182
• Time in Patent Office: 524 Days
• Field of Search: 701/29.3, 701/14, 701/3, 701/29.1, 701/29.9, 701/30.2, 701/31.9, 244/3.1, 244/3.15, 244/75.1, 244/99.8, 244/3.22, 244/3.24, 244/3.27, 244/76.A, 244/175
• US Class Current: 701/3
• CPC Class Codes: F42B 10/38 Range-increasing arrangements F42B10/34, F42B14/06 and F42B15/105 take precedence
• CPC Class Codes: F42B 10/40 with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles
• CPC Class Codes: F42B 10/42 Streamlined projectiles
• CPC Class Codes: F42B 10/668 Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow
• CPC Class Codes: F42B 15/01 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 Class Codes: G05D 1/107 specially adapted for missiles

Abstract

The present invention relates to a missile or munition with a hierarchical, modular, closed-loop flow control system, more particularly to aircraft or munition with flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.

Various embodiments of the flow control system involve elements including flow sensors, active flow control devices or activatable flow effectors, and logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on the surfaces of a missile or munition. The active flow control device or activatable flow effectors create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

Claims

1. A missile or a munition comprising:

a. an aerodynamic surface or surfaces;

b. at least two air flow control zones on one or more aerodynamic surfaces of the missile or munition, at least one of the at least two air flow control zones comprising at least one activatable flow effector capable of being activated and deactivated, wherein the at least one activatable flow effector is deactivated when the activatable flow effector is flush or nearly flush to the aerodynamic surface or surfaces of the missile or munition on or in which the activatable flow effector is located;

c. one or more digital logic devices, the digital logic devices having a separate local, closed loop control system for each flow control zone for activating and deactivating the at least one activatable flow effector to, in part, maneuver the missile or munition, and a global control system to coordinate the local control systems; and

d. a health monitoring system comprising at least one pattern recognition algorithm and at least one decision system and an output,

wherein the health monitoring system output is passed to a user interface and/or to an adaptation algorithm.

2. The missile or munition in claim 1, wherein the at least one activatable flow effector is operated in a binary manner, and is capable of operating at a frequency of at least 1 Hz.

3. The missile or munition in claim 1, further comprising at least one sensor having a signal, wherein the separate local, closed loop control system activates and deactivates the at least one activatable flow effector based on at least in part the signal of the at least one sensor.

4. The missile or munition in claim 3, wherein the separate local closed loop control system monitors the at least one activatable flow effector and/or the at least one sensor and adjusts an output to take into account a lower performance or a failure of either the at least one activatable flow effector;

or the at least one sensor.

5. The missile or munition in claim 3, further comprising a means for determining a relative spatial orientation of the flow effectors and/or sensors on the missile or munition.

6. The missile or munition in claim 1 wherein the global control system calculates, estimates or predicts a desired moment for the aerodynamic surface or surfaces and outputs a signal corresponding to a desired local moment to the local closed loop control system for at least one of the air flow control zones comprising the at least one activatable flow effector.

7. The missile or munition in claim 1 wherein the activatable flow effector is a deployable flow effector.

8. A missile or a munition comprising:

a. an aerodynamic surface or surfaces;

b. at least two air flow control zones on the aerodynamic surface or surfaces of the missile or munition, at least one of the at least two air flow control zones comprising at least one activatable flow effector capable of being activated and deactivated, wherein the at least one activatable flow effector is deactivated when the activatable flow effector is flush or nearly flush to the aerodynamic surface or surfaces of the missile or munition on or in which the activatable flow effector is located; and

c. one or more digital logic devices, the digital logic devices having a separate local, closed loop control system for each flow control zone for activating and deactivating the at least one activatable flow effector to, in part, maneuver the missile or munition, and a global control system to coordinate the local control systems.

9. The missile, or munition in claim 8, wherein the at least one activatable flow effector is operated in a binary manner, and is capable of operating at a frequency of at least 1 Hz.

10. The missile or munition in claim 8, further comprising at least one sensor having a signal, wherein the separate local, closed loop control system activates and deactivates the at least one activatable flow effector based on at least in part the signal of the at least one sensor.

11. The missile or munition in claim 10, wherein the separate, local closed loop control system monitors the at least one activatable flow effector, and/or the at least one sensor and adjusts an output to take into account a lower performance or a failure of either the at least one flow control device or flow effector or the at least one sensor.

12. The missile, or munition in claim 10, further comprising a means for determining a relative spatial orientation of the flow effectors and/or sensors on the missile or munition.

13. The missile or munition in claim 8, wherein the global control system calculates, estimates or predicts a desired moment for the aerodynamic surface or surfaces and outputs a signal corresponding to a desired local moment to the separate, local closed loop control system for the at least one air flow control zones comprising the at least one activatable flow effector.

14. The missile, or munition in claim 8, comprising at least six flow control zones wherein at least two flow control zones comprise at least one activatable flow effectors activated or deactivated by the separate local, closed loop control system.

15. A missile or a munition comprising:

a. an aerodynamic surface or surfaces;

b. at least two air flow control zones on one or more aerodynamic surface or surfaces of the missile or munition;

at least one of the air flow control zones comprising at least one activatable flow effector that is activated and deactivated, wherein the at least one activatable flow effector is deactivated when the activatable flow effector is flush or nearly flush to the aerodynamic surface or surfaces of the missile or munition on or in which the activatable flow effector is located, selected from the group consisting of active vortex generators, which are deployable or create pressure active regions by suction or air pressure;

pulsed vortex generators, plasma actuators;

wall turbulators;

active porosity; and

thermal actuators;

c. one or more digital logic devices, the digital logic devices having a separate local, closed loop control system for each flow control zone, and a global control system to coordinate the separate, local control systems.

16. The missile or munition in claim 15 wherein the separate local, closed loop control system activates and deactivates the at least one deployable flow effector based on at least in part a signal of at least one sensor.

17. The missile or munition in claim 15 wherein the at least one activatable flow effector is operated in a binary manner, and is capable of operating at a frequency of at least 1 Hz.

18. The missile or munition in claim 16, wherein the control system monitors the at least one deployable flow effector and/or at least one sensor and adjusts an output to take into account a lower performance or a failure of either the at least one deployable flow effector or the at least one sensor.

19. The missile or munition in claim 16, further comprising a means for determining a relative spatial orientation of the flow effectors and/or sensors on the missile or munition.

20. The missile or munition in claim 16, wherein the global control system calculates, estimates or predicts a desired moment for the aerodynamic surface or surfaces and outputs a signal corresponding to a desired local moment to the separate, local closed loop control system for the at least one air flow control zones comprising the at least one activatable flow effector.