Anti-missile defense suite

• US 8,066,218 B2
• Filed: 06/10/2004
• Issued: 11/29/2011
• Est. Priority Date: 06/13/2003
• Status: Expired due to Fees

• 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: Rubin, Eugene S.
• Primary Examiner(s): Collins; Timothy D
• Assistant Examiner(s): Bonzell; Philip J
• Application Number:
  US10/560,767
• Publication Number:
  US 20060249009A1
• Time in Patent Office: 2,728 Days
• Field of Search: 244/1.R, 244/1.TD, 244/121, 244/129.1, 102/336, 342/6, 342/9, 342 13- 16
• US Class Current: 244/1.TD
• 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: F41J 2/02 Active targets transmitting infrared radiation
• CPC Class Codes: F41J 9/10 towed

Abstract

A system and method for an aircraft (10) that provides an IR decoy (12) for an incoming missile (18) to track instead of an engine (14) of the aircraft (10) is disclosed. The IR decoy (12) is deployed during or just after take off, and prior to landing to provide a signature (16) for any incoming missile (18). The IR decoy (12) provides a heat source (16) that has a higher radiant intensity than the hottest heat source on the aircraft (10), which is typically the engine (14), thereby providing a more attractive heat source for the missile (18). In another embodiment, a warning system (20) for an aircraft (10) detects an incoming missile (18), and deploys IR decoy (12) and creates an engine mask (22) by injecting an additive into the exhaust stream of the engine (14), thereby obscuring the radiation emanating from the engine (14).

Claims

1. A method for producing a decoy infrared signature to direct an incoming infrared guided missile away from an aircraft infrared signature and to the decoy infrared signature, the method comprising:

deploying a towed IR decoy during at least one aircraft flight time period including aircraft take off and aircraft landing;

powering the towed IR decoy by a laser source located within said aircraft;

amplifying said laser source with an amplifier located within said aircraft to produce an IR decoy infrared signature;

wherein the IR decoy infrared signature is of a magnitude greater than the infrared signature of said aircraft, and wherein said IR decoy infrared signature includes infrared energy in more than one spectral band;

distributing the IR decoy infrared signature by means of a plurality of optical fibers of various lengths coupled to a plurality of small apertures within the IR decoy;

detecting an incoming infrared guided missile with a warning system, and responsive to said detecting, further including the act of masking an infrared signature of at least one engine of the aircraft by causing a first amount of exhaust obscurant to be added into an exhaust stream of said at least one engine of the aircraft; and

retracting the towed IR decoy after the aircraft reaches an altitude that is beyond a range of an infrared guided missile or proximate the time immediately preceding or after the aircraft has landed.

2. The method for producing a decoy infrared signature to direct an incoming infrared guided missile away from an aircraft according to claim 1, wherein the act of retracting the towed IR decoy after take off is performed at approximately 10,000 feet.

3. The method for producing a decoy infrared signature to direct an incoming infrared guided missile away from an aircraft according to claim 1, further comprising deploying the towed IR decoy when the warning system has detected the incoming infrared guided missile, and retracting the towed IR decoy when the warning system is not detecting the incoming infrared guided missile.

4. The method for producing a decoy infrared signature to direct an incoming infrared guided missile away from an aircraft according to claim 1, further comprising repeating the detecting act to detect the incoming infrared guided missile with the warning system;

and responsive to said repeated detecting act, increasing the magnitude of the towed IR decoy by rapid modulation of the laser source.

5. The method for producing a decoy infrared signature to direct an incoming infrared guided missile away from an aircraft according to claim 4, further comprising increasing the first amount of the exhaust obscurant added into said exhaust stream of said at least one engine of the aircraft in response to said detecting act.

6. An aircraft system for producing a decoy infrared signature to direct an incoming infrared guided missile away from an aircraft infrared signature and to the decoy infrared signature, the system comprising:

a towed IR decoy, for producing the decoy infrared signature;

a photonic source located within said aircraft powering a plurality of fiber optic cables, said plurality of fiber optic cables having various lengths, each varying length fiber optic cable having a terminating point at a predetermined distance from a terminating point of one or more other of said plurality of fiber optic cables, for directly radiating IR energy into the atmosphere from the terminating points, wherein the various lengths of fiber optic cables and distance between said terminating points provides said decoy infrared signature,

an amplifier located with said aircraft wherein the amplifier amplifies said IR decoy infrared signature to a magnitude greater than the infrared signature of said aircraft, and wherein said IR decoy infrared signature includes infrared energy in more then one spectral band;

a warning system, for detecting an incoming infrared guided missile;

an aircraft engine obscurant system, responsive to said detection of said incoming infrared guided missile from said warning system, for masking an infrared signature of at least one engine of said aircraft by causing a first amount of exhaust obscurant to be added into an exhaust stream of said at least one engine of the aircraft; and

a deployment and retraction device, for deploying and set retracting the towed IR decoy proximate at least one tithe period including at least aircraft take off and aircraft landing.

7. The aircraft system according to claim 6, wherein the photonic source is a high power fiber laser.

8. The aircraft system according claim 6, wherein the IR decoy includes a heat source.

9. An aircraft system for detecting and avoiding an incoming infrared guided missile, the system comprising:

a warning system, for detecting an incoming infrared guided missile;

a towed IR decoy, coupled to a laser source, the laser source being located within the aircraft, for producing a decoy infrared signature, said towed IR decoy coupled to said laser source within the aircraft by way of a plurality of fiber optic cables, wherein said plurality of fiber optic cables have various lengths, each varying length fiber optic cable having a terminating point a distance from a terminating point of one or more other of said plurality of fiber optical cables, for directly radiating IR energy into the atmosphere from the terminating points, wherein the various lengths of fiber optic cables and distance between said terminating points provides said decoy infrared signature;

an amplifier located within the aircraft wherein the amplifier amplifies said IR decoy infrared signature to a magnitude greater than an infrared signature of said aircraft, and wherein said IR decoy infrared signature includes infrared energy in more than one spectral band;

a deployment and retraction device, for deploying the towed IR decoy when the warning system has detected the incoming missile, and for retracting the towed IR decoy when the warning system is not detecting the incoming missile; and

an aircraft engine obscurant system, responsive to said detection of said incoming infrared guided missile from said warning system, for masking an infrared signature of at least one engine of the aircraft by causing a first amount of exhaust obscurant to be added into an exhaust stream of said at least one engine of the aircraft.

10. The aircraft system according to claim 9, wherein the exhaust obscurant includes an additive that is selected from a group consisting of oil, graphite-oil, multispectral water or a commercial oil smoke generator.

11. The aircraft system according to claim 9, wherein said fiber optic cables at various lengths provide an extended IR signature to produce said IR decoy infrared signature.

12. The aircraft system according to claim 9, wherein the towed IR decoy includes heat source.

13. The aircraft system according to claim 9, wherein said laser source is a high power fiber laser.