[특허]Modular divert and attitude control system

Raytheon Company

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Modular divert and attitude control system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41G-007/00 F42B-015/01 F42B-015/00
미국특허분류(USC)	244/003.1; 060/200.1; 060/204; 060/224; 060/225; 060/253; 102/283; 244/003.15; 244/003.21; 244/003.22
출원번호	US-0484986 (2009-06-15)
등록번호	US-8242422 (2012-08-14)
발명자 / 주소	Olden, Thomas A. Cavalleri, Robert J.
출원인 / 주소	Raytheon Company
대리인 / 주소	Gifford, Eric A.
인용정보	피인용 횟수 : 6 인용 특허 : 28

초록

There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.

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1. A vehicle, comprising: a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges; anda processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors. 2. The vehicle of claim 1, wherein each multiple-impulse rocket motor further comprises: a nozzle, anda plurality of combustion chambers coupled to the nozzle, whereineach of the plurality of combustion chambers at least partially encloses a respective solid fuel propellant charge, anda gas path from each solid fuel propellant charge to the nozzle is obstructed, prior to ignition of the solid fuel propellant charge, by an asymmetrical burst disk. 3. The vehicle of claim 2, wherein at least some of the multiple-impulse rocket motors further comprise: a gas reservoir coupled to accumulate combustion gases produced by combustion of one or more of the propellant charges; anda valve to control the flow of gases from the gas reservoir to the nozzle,wherein the processor provides commands to open and close the valve, andwherein each burst disc is disposed between the respective solid fuel propellant charge and the gas reservoir. 4. The vehicle of claim 3, wherein at least some of the plurality of multiple-impulse rocket motors are pellet-loaded multiple-impulse rocket motors. 5. The vehicle of claim 1, wherein the plurality of multiple-impulse rocket motors includes a plurality of divert motors. 6. The vehicle of claim 5, wherein the plurality of divert motors consists of four divert motors, which are disposed in a plane that is normal to a longitudinal axis of the vehicle and proximate to a center of mass of the vehicle, andoriented to generate thrust in radial directions separated by 90-degree intervals. 7. The vehicle of claim 1, wherein the plurality of multiple-impulse rocket motors includes a plurality of attitude thrusters. 8. The vehicle of claim 7, wherein the plurality of attitude thrusters are disposed in positions remote from a plane that is normal to a longitudinal axis of the vehicle and proximate to a center of mass of the vehicle, andoriented to generate thrust outward from the longitudinal axis in respective directions including radial directions and non-radial directions. 9. The vehicle of claim 1 wherein the processor generates the at least one command based on signals received from one or more of a seeker subsystem, a communications subsystem, and a navigation subsystem. 10. The vehicle of claim 9, wherein the seeker subsystem tracks a target,the processor generates commands to maneuver the vehicle onto a trajectory to intercept the target based on guidance signals from the seeker subsystem. 11. A method of controlling the trajectory of a vehicle, comprising: determining a thrust required to effect a change from a present trajectory to a desired trajectory;selecting one or more solid fuel propellant charges collectively adapted to produce the required thrust; andigniting the one or more selected solid fuel propellant charges, whereineach selected solid fuel propellant charge is one of a plurality of solid fuel propellant charges within one of a plurality of multiple-impulse rocket motors. 12. The method of claim 11, wherein at least some of the plurality of multiple-impulse rocket motors include gas storage reservoirs,igniting the one or more selected solid fuel propellant charge causes one or more gas reservoirs to accumulate combustion gases, andthe method further comprises opening respective values coupled to the one or more gas reservoirs to exhaust combustion gases to produce the required thrust. 13. The method of claim 12, further comprising: tracking a target,wherein the desired trajectory causes the vehicle to intercept the target. 14. The method of claim 12, wherein the method is performed continuously and in real time. 15. A method of maneuvering a vehicle having a plurality of multiple-impulse rocket motors disposed to control a trajectory and an attitude of the vehicle, each multiple-impulse rocket motor including a plurality of independently-ignitable solid fuel charges, the method comprising: determining a thrust required to effect a required change in at least one of the trajectory of the vehicle and the attitude of the vehicle;selecting one or more solid fuel propellant charges collectively adapted to produce the required thrust; andigniting the one or more selected solid fuel propellant charges. 16. The method of claim 15, wherein igniting the one or more selected solid fuel propellant charge causes one or more gas reservoirs to accumulate combustion gases, the method further comprising: opening one or more values coupled to respective gas reservoirs to exhaust combustion gases to produce the required thrust;each selected solid fuel propellant charge is one of a plurality of solid fuel propellant charges within one of a plurality of multiple-impulse rocket motors. 17. The method of claim 15, further comprising: tracking a targetdetermining the change in the trajectory of the vehicle required to maneuver the vehicle to intercept the target.

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이 특허를 인용한 특허 피인용횟수: 6

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Modular divert and attitude control system

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Modular divert and attitude control system

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이 특허에 인용된 특허 (28)

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