Distributed infrared countermeasure installation for fixed wing aircraft

• US 20090173822A1
• Filed: 08/11/2008
• Published: 07/09/2009
• Est. Priority Date: 01/07/2008
• Status: Abandoned Application

• Current Assignee: BAE Systems Information and Electronic Systems Integration Incorporated (BAE Systems Plc)
• Original Assignee: BAE Systems Information and Electronic Systems Integration Incorporated (BAE Systems Plc)
• Inventors: Raab, Martin, Ferrari, John, Chew, Christopher L., Hoff, George J., Rusch, James, Kravitz, Arnold, Smith, Donald K.
• Application Number:
  US12/228,510
• Publication Number:
  US 20090173822A1
• Time in Patent Office: Days
• US Class Current: 244/1.R
• CPC Class Codes: B64D 7/00 Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft dropping bombs or the like B64D1/00; armaments or mountings therefor per se F41
• CPC Class Codes: F41H 11/02 Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems cartridges or missiles for producing smoke or for dispensing radar chaff or infrared material F42B5/15, F42B12/48, F42B12/70; informative reference: details of radar or sonar systems G01S7/00; jamming or electronic countermeasures G01S7/38, G01S7/495, H04K3/00
• CPC Class Codes: F41H 13/0056 for blinding or dazzling, i.e. by overstimulating the opponent's eyes or the enemy's sensor equipment

Abstract

A distributed aircraft defense system involving infrared countermeasures is installed in a distributive fashion for commercial aircraft, typically fixed wing aircraft, in which maintenance downtime is minimized due to the ability to access, remove, test, fix and/or replace individual modules within the distributed system.

Claims

1. Apparatus for airliner defense comprising:

A distributed aircraft defense system having modules spaced from one another and located within the aircraft, each of the modules being accessible for maintenance, whereby maintenance may be performed on the aircraft defense system at remote locations, with standard aircraft maintenance personnel and in timeframes commensurate with commercial airline operations.

2. The apparatus of claim 1, wherein said modules have inputs and outputs having input and output tolerances that are designed for broad interoperability, such that the modules may be interconnected without alignment or specialized interfaces.

3. The apparatus of claim 2, wherein said modules are initially designed with broad input and output tolerances.

4. The apparatus of claim 1, wherein said modules are not mechanically aligned one with the other.

5. The method of claim 1, wherein said modules are selected from modules associated with a common missile warning system.

6. The apparatus of claim 5, wherein the common missile warning system includes ultraviolet sensors for sensing the associated emissions from a rocket motor exhaust.

7. The apparatus of claim 1, wherein said modules include at least one of a warning sensor, a control processor, a laser, a laser pointer tracker, and a pointer tracker controller.

8. The apparatus of claim 1, wherein said modules include warning sensors, a control processer, a laser, a pointer tracker, and a pointer tracker controller, each separated one from the other and interconnected without specialized interfaces and without relying on an optical bench.

9. The apparatus of claim 1, wherein each of said modules can be handled by an individual due to the weight thereof.

10. The apparatus of claim 1, wherein said modules include internally carried modules with the exception of a pointer tracker which extends from the fuselage of the aircraft and at least one sensor which extends from the fuselage of the aircraft, whereby turbulent airflow resulting from said aircraft defense system is minimized.

11. A method for defending an airliner against attack by a missile to minimize maintenance downtime comprising:

installing a distributed infrared countermeasure system within the aircraft with the system including a number of modules spaced about the aircraft and accessible by an individual for the maintenance, testing, repair and/or replacement thereof by a single individual without the use of specialized handling equipment.

12. The method of claim 11, wherein the modules are specifically configured with tolerances to assure interoperability with other modules on the system without having to utilize a common rigid mechanical support for all of the modules.

13. The method of claim 12, wherein the modules are distributed throughout the aircraft and are secured without the use of an optical bench.

14. The method of claim 12, wherein said modules include a pointer tracker, which extends from the fuselage of the aircraft and provides only minimal drag, the other modules being solely within the fuselage of the aircraft, with the exception of one or more sensors that protrude from the aircraft a minimal amount.

15. The method of claim 12, wherein the modules include at least one of a warning sensor, a control processor, a laser, a pointer tracker, and a pointer tracker control.

16. The method of claim 15, wherein the modules can be maintained by removal, inspection, repair or replacement by a single individual without the use of specialized handling equipment.

17. The method of claim 12, wherein the use of the distributed system permits limiting the weight of an individual module such that it can be removed, tested, repaired or replaced without the necessity of removal of any of the other modules.

18. A system for defending an aircraft against incoming missiles fired from the ground which is easily maintainable in the field using standard aircraft maintenance personnel, avoiding the use of a pod carried on the belly of the aircraft in which all of the countermeasure equipment is carried in the pod and in which the pod must be removed for maintenance procedures, comprising:

a number of modules distributed throughout the aircraft and spaced from one another, with the modules having input and output tolerances that are designed for broad interoperability and interconnected without alignment or specialized interfaces, the modules being distributed throughout the aircraft and being individually maintainable by either access to or removal of the individual modules, the weight of the modules being maintained below that which can be handled by an individual without specialized handling equipment.

19. The system of claim 18, wherein said modules are selected from modules associated with a common missile warning system.

20. The system of claim 19, wherein said common missile warning system includes ultraviolet sensors for sensing the associated emissions from rocket motor exhaust.

21. The system of claim 18, wherein said modules include at least one of a warning sensor, a control processor, a laser, a laser pointer tracker and a pointer tracker controller.

22. The system of claim 18, wherein said modules include a warning sensor, a control processor, a laser, a pointer tracker and a pointer tracker controller.

23. The system of claim 18, wherein said modules include internally carried modules with the exception of a pointer tracker which extends from the fuselage of the aircraft and at least one sensor which extends from the fuselage of the aircraft, whereby turbulence airflow resulting from said system is minimized.