A thermal radiation-generating decoy mounted adjacent an aircraft engine structure, such as an engine nacelle, includes a heat source inside of an aerodynamic enclosure with a mounting interface to attach the enclosure to the engine structure. The decoy can further be located at the lower extreme of
A thermal radiation-generating decoy mounted adjacent an aircraft engine structure, such as an engine nacelle, includes a heat source inside of an aerodynamic enclosure with a mounting interface to attach the enclosure to the engine structure. The decoy can further be located at the lower extreme of and adjacent the forward-most portion of the engine nacelle in order to attract an infrared-seeking threat to the vicinity of the fan containment portion of the engine nacelle. The decoy can be designed to have a thermal signature that mimics a scaled overall aircraft thermal signature. In addition, the decoy can include a fuse shield adjacent the enclosure to detonate a threat in the case that the threat approach trajectory is imprecise and the threat bypasses the enclosure within an aspect of the fuse shield as viewed from the approach direction of the threat.
대표청구항▼
What is claimed is: 1. A decoy mountable adjacent an aircraft engine structure, comprising: a heat source; an enclosure that at least partially encloses the heat source, wherein the enclosure is mounted below a forward portion of the engine structure to attract an infrared-seeking threat; and a fus
What is claimed is: 1. A decoy mountable adjacent an aircraft engine structure, comprising: a heat source; an enclosure that at least partially encloses the heat source, wherein the enclosure is mounted below a forward portion of the engine structure to attract an infrared-seeking threat; and a fuse shield disposed below the enclosure, the fuse shield comprising a panel that extends downward from the enclosure and along an axis of the engine structure. 2. The decoy of claim 1, wherein the enclosure is mounted approximately on an opposite side of the engine structure from a vulnerable aircraft structure. 3. The decoy of claim 1, wherein the engine structure includes an engine nacelle. 4. The decoy of claim 1, wherein the enclosure is mounted approximately adjacent a lower extreme of an engine nacelle. 5. The decoy of claim 1, wherein the enclosure is mounted directly below a forward portion of an engine nacelle. 6. The decoy of claim 1, wherein the enclosure is mounted to a fan containment portion of an engine nacelle. 7. The decoy of claim 1, wherein the enclosure is mounted such that the enclosure protrudes at least partially forward of an engine nacelle. 8. The decoy of claim 1, wherein the heat source includes a burner that combusts a same type of fuel as an aircraft engine. 9. The decoy of claim 1, wherein the decoy has a thermal signature at least partially based on an aircraft thermal signature. 10. The decoy of claim 9, wherein the enclosure includes a shape configured to create the thermal signature. 11. The decoy of claim 1, wherein the enclosure comprises a substantially thermal radiation-transparent portion. 12. The decoy of claim 1, wherein the decoy is configured to attract a shoulder-fired missile. 13. The decoy of claim 1, further comprising a fuse shield fixedly coupled adjacent the enclosure to detonate the threat in the case that the threat bypasses the enclosure within an aspect of the shield. 14. A decoy comprising: a fuse shield mounted to an engine nacelle of an aircraft, the fuse shield including an airfoil panel extending downward from a forward portion of the engine and in line with an axis of the engine nacelle; a heat source; and an enclosure that at least partially encloses the heat source, wherein the enclosure is mounted to a body portion of the fuse shield, the enclosure being disposed below and forward to the engine and the enclosure extending outward from both sides of the fuse shield to attract an infrared-seeking threat. 15. The decoy of claim 14, wherein the fuse shield has a relatively large lateral aspect and a relatively small frontal aspect. 16. The decoy of claim 14, wherein the fuse shield extends aft but not forward of the enclosure. 17. The decoy of claim 14, wherein the fuse shield includes a frangible material. 18. The decoy of claim 14, wherein the fuse shield includes a substantially thermal radiation-transparent portion such that a radiation field of the decoy remains substantially unblocked by the fuse shield. 19. A decoy comprising: means for generating heat; means for enclosing the heat-generating means, wherein the means for enclosing is mounted below a forward portion of an engine nacelle of an aircraft to attract an infrared-seeking threat; and a fuse shielding means disposed below the enclosure, the fuse shielding means comprising a panel that extends downward from the means for enclosing and along an axis of the engine nacelle. 20. The decoy of claim 19, wherein the means for enclosing is mounted approximately adjacent a lower extreme of a forward portion of the engine nacelle. 21. A decoy comprising: a fuse shield means mounted to an engine nacelle of an aircraft, the fuse shield means including an airfoil panel extending downward from a forward portion of the engine nacelle and in line with an axis of the engine nacelle; means for generating heat; means for enclosing the heat-generating means, wherein the means for enclosing is mounted to a body portion of the fuse shield means, the means for enclosing extending outward from both sides of the fuse shield means to attract an infrared-seeking threat. 22. The decoy of claim 21, wherein the fuse shield means comprises pervious means for permitting a radiation field of the decoy to pass substantially unblocked through at least a portion of the fuse shield means.
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이 특허에 인용된 특허 (6)
Czarnecki Gregory J., Aircraft missile-hit survivability using infrared lamp and sacrificial support structure.
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