Weapon active hazard mitigation method

Patent metadata

Field	Value
Publication number	US-11879710-B2
Application number	US-202318335548-A
Country	US
Kind code	B2
Filing date	Jun 15, 2023
Priority date	Dec 17, 2019
Publication date	Jan 23, 2024
Grant date	Jan 23, 2024

Abstract

A mitigation control system, for performing an active hazard mitigation method, is arranged in an environment containing an energetic material and includes an abnormal temperature sensor for detecting an abnormal temperature of the environment, a power source that is mechanically actuated by the abnormal temperature sensor when the abnormal temperature exceeds a predetermined abnormal temperature threshold, a mitigation controller that is actuated by the power source, and a plurality of local temperature sensors that are communicatively coupled to the mitigation controller and are arranged for detecting critical temperatures in specific regions of the environment. The mitigation controller executes a mitigation action when one of the critical temperatures exceeds a predetermined critical temperature threshold for the corresponding specific region.

First claim

What is claimed is:

1. A method for mitigating an active hazard in an air vehicle containing an energetic material, the method comprising:
detecting an abnormal temperature of the air vehicle;
mechanically actuating a power source when the detected temperature exceeds a predetermined temperature threshold;
electrically actuating a mitigation controller after the power source is actuated;
detecting a critical temperature in separate sub-assemblies that are integrated to form the air vehicle after the mitigation controller is actuated; and
executing a mitigation action or technique in at least one of the different sub-assemblies using the mitigation controller when the critical temperature in the corresponding sub-assembly exceeds a predetermined critical temperature threshold.

2. The method of claim 1 , wherein the detecting the abnormal temperature includes detecting the abnormal temperature with a passive temperature sensor.

3. The method of claim 1 , wherein the detecting the abnormal temperature includes detecting the abnormal temperature in an environment around the air vehicle.

4. The method of claim 1 , wherein the detecting the critical temperature includes detecting the critical temperature in one or more active temperature sensors.

5. The method of claim 1 , wherein the detecting the critical temperature includes detecting the critical temperature in one or more temperature sensors that correspond to respective of the different sub-assemblies.

6. The method of claim 1 , wherein different of the sub-assemblies have different critical temperatures.

7. The method of claim 1 ,
wherein the sub-assemblies have respective mitigation subcontrollers; and
wherein the executing the mitigation action or technique includes the mitigation subcontrollers of the at least one of the different sub-assemblies executing the mitigation action or technique for the corresponding of the at least one of the different sub-assemblies.

8. The method of claim 1 , wherein the mitigation action includes mitigation of a hazard from an energetic material.

9. The method of claim 1 , wherein the mitigation action includes mitigation of a hazard from an explosive.

10. The method of claim 1 , wherein the mitigation action includes mitigation of a hazard from a pyrotechnic composition.

11. The method of claim 1 , wherein the mitigation action includes mitigation of a hazard from a fuel and/or oxidizer.

12. The method of claim 1 , wherein the mitigation action includes a passive mitigation action.

13. The method of claim 12 , wherein the passive mitigation action includes at least one of venting, shielding, painting, using shear bolts or stress raisers, and softening a component within an environment of the air vehicle.

14. The method of claim 1 , wherein the mitigation action includes an active mitigation action.

15. The method of claim 14 , wherein the active mitigation action includes one or more of igniting an energetic material below an ignition temperature for the energetic material, using a thermal initiated venting system for fuel release or component cutting, performing a controlled burn, and controlling a location of ignition.

16. The method of claim 1 , wherein the sub-assemblies include a warhead module.

17. The method of claim 1 , wherein the sub-assemblies include a fuel tank module.

18. The method of claim 1 , wherein the sub-assemblies include a jet engine module.

19. The method of claim 1 , wherein the sub-assemblies include a booster module.

20. The method of claim 1 , wherein the air vehicle is a cruise missile.

Assignees

• Raytheon Co

Inventors

• Barents Dennis D
• Christianson Kim L
• Lattimore Aaron C
• Knight Andrew K

Classifications

• F42B15/34 Primary

  Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} · CPC title

• F41A17/06

  Electric or electromechanical safeties (F41A17/04, F41A17/08 take precedence) · CPC title

• F42B12/207

  characterised by the explosive material or the construction of the high explosive warhead, e.g. insensitive ammunition · CPC title

• F42B15/36

  Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means · CPC title

• F42B39/14

  Explosion or fire protection arrangements on packages or ammunition (F42B39/20 {and F42B39/24} take precedence; {wall or panel structure of fireproof safes or storage containers E05G1/024}) · CPC title