[특허]Missile system with multiple submunitions

Raytheon Company

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Missile system with multiple submunitions

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-012/56 F42B-010/60 F42B-010/00 F42B-015/01 F41G-007/00
미국특허분류(USC)	244/003.15; 244/003.1; 244/003.11; 244/003.14; 244/003.19; 244/003.21; 089/001.11
출원번호	US-0376192 (2003-02-27)
발명자 / 주소	Spate, Wayne V. Schneider, Arthur J. McFarland, Michael B.
출원인 / 주소	Raytheon Company
대리인 / 주소	Renner, Otto, Boisselle & Sklar, LLP
인용정보	피인용 횟수 : 17 인용 특허 : 7

초록

A multi-staged missile includes a booster and a submunition delivery vehicle that has one or more submunitions. The booster rapidly accelerates the submunition vehicle, and then separates from the submunition vehicle. The submunition delivery vehicle is then maneuvered to approach a target. Individual submunitions finally separate, and are individually guided to the target. By providing multiple, independently-targeted submunitions, the missile greatly increases the chances of hitting the target.

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1. A missile for hitting a moving target, the missile comprising:a booster; anda submunition delivery vehicle separably coupled to the booster;wherein the submunition delivery vehicle includes:at least one submunition separable from the submunition delivery vehicle; anda beacon separably coupled to the at least one submunition; andwherein the beacon is configured to emit a signal indicating position of the submunition delivery vehicle. 2. The missile of claim 1, wherein the booster includes a thrust vectoring system. 3. The missile of claim 2, wherein the thrust vectoring system includes jet vanes. 4. The missile of claim 2, wherein the thrust vectoring system includes one or more thrust vectoring nozzles. 5. The missile of claim 1,wherein the submunition delivery vehicle includes an aerodynamic control section slidable along the submunition delivery vehicle; andwherein the aerodynamic control section includes multiple fins. 6. The missile of claim 1, wherein the at least one submunition includes multiple independently-maneuverable submunitions. 7. The missile of claim 6, wherein the submunitions are arrayed in line along an axis of the submunition delivery vehicle. 8. The missile of claim 7, wherein each of the submunitions includes a tail cavity capable of receiving a nose of another of the submunitions. 9. The missile of claim 6, wherein the submunitions each include an articulatable nose. 10. The missile of claim 9, wherein each of the submunitions further includes:a nose actuator operatively coupled to the nose to position the nose; andcontroller electronics operatively coupled to the nose actuator to control steering of the submunition. 11. The missile of claim 10,wherein the controller electronics are operatively coupled to a receiver for receiving information from a remote location; andwherein the information is used in positioning the nose. 12. The missile of claim 6, wherein the submunitions are substantially identical with each other. 13. The missile of claim 6, wherein the submunitions each include deployable fins. 14. The missile of claim 1, wherein the beacon is included in a submunition delivery vehicle tail section that is part of the submunition delivery vehicle. 15. The missile of claim 14, wherein the tall section also includes:an antenna for receiving control signals; andcontroller electronics coupled to the antenna. 16. The missile of claim 15, wherein the controller is operatively coupled to an articulatable nose of one of the at least one submunition, for steering the submunition delivery vehicle. 17. The missile of claim 1, wherein the missile is a surface-to-air missile used to neutralize an incoming missile. 18. A missile for hitting a moving target, the missile comprising:a booster; anda submunition delivery vehicle separably coupled to the booster;wherein the submunition delivery vehicle includes:multiple independently-maneuverable submunitions; anda beacon coupled to the submunitions;wherein the beacon is configured to emit a signal indicating position of the submunition delivery vehicle;wherein the submunitions each include:an articulatable nose;a nose actuator operatively coupled to the nose to position the nose;controller electronics operatively coupled to the nose actuator to control steering of the submunition;a beacon configured to emit a signal indicating position of the submunition;a tail cavity capable of receiving a nose of another of the submunitions; anddeployable fins; andwherein the submunitions are arrayed in line along an axis of the submunition delivery vehicle. 19. The missile of claim 18,wherein the submunition delivery vehicle includes an aerodynamic control section slidable along the submunition delivery vehicle; andwherein the aerodynamic control section includes multiple fins. 20. A method of hitting a moving target using a missile, comprising:accelerating the missile using a booster of the missile;separating the booster from a submunition delivery vehicle of the missile, wh erein the submunition delivery vehicle includes multiple independently-guidable submunitions;separating the submunitions from the submunition delivery vehicle; and independently guiding the submunitions to the moving target;wherein the independently guiding includes steering the submunitions by positioning respective articulatable noses of the submunitions.

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Missile system with multiple submunitions

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Missile system with multiple submunitions

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이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 17

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