[특허]Guided munition systems including combustive dome covers and methods for equipping guided munitions with the same

Raytheon Company

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특허 상세정보

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Guided munition systems including combustive dome covers and methods for equipping guided munitions with the same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41G-007/22 H01Q-001/42 F41G-007/00 H01Q-001/00
미국특허분류(USC)	244/003.16; 244/003.1; 244/003.15; 244/003.19; 343/872
출원번호	US-0917705 (2010-11-02)
등록번호	US-8445823 (2013-05-21)
발명자 / 주소	Williams, Darin S. Wright, Richard J.
출원인 / 주소	Raytheon Company
대리인 / 주소	Gifford, Eric A.
인용정보	피인용 횟수 : 1 인용 특허 : 6

초록

Embodiments of a guided munition system are provided, as are embodiments of a combustive dome cover and methods for equipping a guided munition with a combustive dome cover. In one embodiment, the guided munition system includes a guided munition, which has a munition body and a seeker dome coupled thereto, and a combustive dome cover disposed over the seeker dome. The combustive dome cover is configured to uncover the seeker dome at a predetermined time of deployment and to combust when so deployed to minimize the production of debris.

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1. A guided munition system, comprising: a guided munition, comprising: a munition body; anda seeker including one or more electromagnetic radiation sensors; anda seeker dome through which electromagnetic signals are received and passed to the seeker, said seeker dome coupled to the munition body; anda combustive dome cover disposed over the seeker dome to physically shield the seeker dome from potential sources of contamination, the combustive dome cover configured to uncover the seeker dome at a predetermined time of deployment prior to seeker operation and to combust when so deployed to minimize the production of debris. 2. A guided munition system according to claim 1 wherein the heating feature comprises an aerodynamic heating structure projecting from the combustive dome cover and configured to generate heat during munition flight to auto-ignite the combustive dome cover. 3. A guided munition system according to claim 2 wherein the aerodynamic heating feature comprises a substantially conically-shaped nose portion extending from the combustive dome cover. 4. A guided munition system according to claim 2 wherein the aerodynamic heating structure is integrally formed with the combustive dome cover. 5. The guided munition system according to claim 1 further comprising a heating feature thermally coupled to the combustive dome cover to generate a sufficient heat quantity at the predetermined time of deployment to initiate combustion of the dome cover to minimize the production of debris. 6. A guided munition system comprising: a guided munition, comprising: a munition body; anda seeker dome coupled to the munition body;a combustive dome cover disposed over the seeker dome; anda heating feature thermally coupled to the combustive dome cover,the combustive dome cover configured to uncover the seeker dome at a predetermined time of deployment and to combust when so deployed to minimize the production of debris. 7. A guided munition system, comprising: a guided munition, comprising: a munition body; anda seeker dome con led to the munition body;a combustive dome cover disposed over the seeker dome; andan ignition device coupled to the combustive dome cover,the combustive dome cover configured to uncover the seeker dome at a predetermined time of deployment and to combust when so deployed to minimize the production of debris. 8. A guided munition system according to claim 7 wherein the combustive dome cover comprises: a first cover piece; anda second cover piece coupled to the first cover piece to enclose the seeker dome. 9. A guided munition system according to claim 8 wherein the first and second cover pieces are configured to separate during munition flight, and wherein the ignition device is actuated by separation of the first and second cover pieces. 10. A guided munition system according to claim 9 wherein the ignition device is mounted to the first cover piece, and wherein the guided munition system further comprises an elongated connective member coupling the ignition device to the second cover piece. 11. A guided munition system according to claim 7 further comprising a drag-generating member coupled to the ignition device and configured to actuate the ignition device at a predetermined airspeed during munition flight. 12. A guided munition system according to claim 7 wherein the ignition device is at least partially embedded in the combustive dome cover. 13. A guided munition system according to claim 7 wherein the ignition device comprises a signal-actuated squib. 14. A guided munition system according to claim 13 further comprising an electrical conductor operably coupled to the signal-actuated squib and accessible from the exterior of the combustive dome cover to enable actuation of the signal-actuated squib by an externally-generated ignition signal. 15. A guided munition system according to claim 13 wherein the guided munition further comprises an ignition controller disposed within the munition body and operably coupled to the signal-actuated squib, the ignition controller configured to actuate the signal-actuated squib at a desired time of deployment. 16. A guided munition system, comprising: a guided munition, comprising: a munition body; anda seeker dome coupled to the munition body; anda combustive dome cover disposed over the seeker dome, the combustive dome cover comprising an inner combustive liner and an outer inert layer disposed over the inner combustive liner, the combustive dome cover configured to uncover the seeker dome at a predetermined time of deployment and to combust when so deployed to minimize the production of debris. 17. A guided munition system according to claim 16 wherein the inner combustive liner comprises nitrocellulose. 18. A guided munition system according to claim 16 further comprising an outer ablative coating formed over the outer inert layer. 19. A combustive dome cover, comprising: an inner combustive liner configured to ignite when exposed to a predetermined ignition temperature; andan outer inert layer disposed over the inner combustive liner and configured to combust in conjunction with the inner combustive liner after ignition thereof. 20. A combustive dome cover according to claim 19 wherein the combustive dome cover is configured to be utilized in conjunction with a guided munition including a seeker dome, and wherein outer inert layer comprises a substantially rigid shell disposed over the seeker dome to shield the seeker dome from exposure to external contaminants. 21. A method for equipping a guided munition with a combustive dome cover, the method comprising the steps of: fabricating a combustive dome cover configured to combust when exposed to a predetermined ignition temperature;coupling a heating feature to the combustive dome cover; andpositioning the combustive dome cover over a seeker dome included within the guided munition. 22. The method according to claim 21 wherein the heating feature comprises an ignition device. 23. The method according to claim 21 wherein the heating feature comprises an aerodynamic heating structure projecting from the combustive dome cover and configured to generate heat during munition flight to auto-ignite the combustive dome cover. 24. A guided munition system, comprising: a guided munition, comprising: a munition body; anda seeker dome coupled to the munition body;a combustive dome cover disposed over the seeker dome, the combustive dome cover configured to uncover the seeker dome at a predetermined time of deployment; anda heating feature thermally coupled to the combustive dome cover to generate a sufficient heat quantity at the predetermined time of deployment to initiate combustion of the dome cover to minimize the production of debris. 25. The guided munition system according to claim 24, wherein the heating feature comprises an ignition device. 26. The guided munition system according to claim 24, wherein the heating feature comprises an aerodynamic heating structure projecting from the combustive dome cover and configured to generate heat during munition flight to auto-ignite the combustive dome cover.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

Edwards, Jeffrey C. Aerial vehicle with combustible time-delay fuse. USP2015099121668.

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Guided munition systems including combustive dome covers and methods for equipping guided munitions with the same

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Guided munition systems including combustive dome covers and methods for equipping guided munitions with the same

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이 특허에 인용된 특허 (6)

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