Evolvable propulsion module
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0635607
(2000-08-10)
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발명자
/ 주소 |
- Soranno Kevin A.
- Younkin David L.
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출원인 / 주소 |
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대리인 / 주소 |
Harness, Dickey & Pierce, P.L.C.
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인용정보 |
피인용 횟수 :
9 인용 특허 :
2 |
초록
▼
A spacecraft propulsion module (16) that includes an outer cylindrical housing (20), an end wall (22) and a specialized internal structure (50) that is capable of supporting various spacecraft components (110, 112, 124), to provide different levels of spacecraft complexity for different missions. Th
A spacecraft propulsion module (16) that includes an outer cylindrical housing (20), an end wall (22) and a specialized internal structure (50) that is capable of supporting various spacecraft components (110, 112, 124), to provide different levels of spacecraft complexity for different missions. The internal structure (50) within the housing (20) includes a plurality of inner walls (52-58) defining an "eggcrate" structure. The plurality of inner walls (52-58) includes a first pair of walls (52, 54), extending in one direction and a second pair of walls (56, 58) extending in a substantially orthogonal direction to define a center compartment (76) surrounded by a plurality of perimeter compartments (60-74). The inner walls (52-58) and the outer housing (20) define support surfaces on which can be mounted different spacecraft components, such as propellant tanks (110), pressurant tanks (168), life support tanks (126), control, guidance, navigation and communication avionics (124), batteries (112), etc. depending on the particular spacecraft design. The outer surface of the cylinder housing (20) and end wall (22) provide a significant amount of surface area for mounting engines (36) and thrusters (38) to give the module (16) free flying capability for both four and six degrees of freedom. The intersection of the inner walls (52-58) gives the spacecraft module (16) four inner mounting points (80-86) and the intersection of the inner walls (52-58) with the outer housing (20) gives the spacecraft eight outer mounting points (88-102). These mounting points (80-102) gives the spacecraft module versatility to attach different types of mounting adapters (42, 44, 46, 164) to connect other spacecraft modules to the propulsion module (16), such as crew modules, cargo modules, equipment modules, additional propulsion modules, etc.
대표청구항
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[ What is claimed is:] [1.]1. A method of designing a spacecraft where the design evolves to different spacecraft having different intended space mission types, said method comprising the steps of:designing a first evolution spacecraft for one spacecraft mission, said first evolution spacecraft bein
[ What is claimed is:] [1.]1. A method of designing a spacecraft where the design evolves to different spacecraft having different intended space mission types, said method comprising the steps of:designing a first evolution spacecraft for one spacecraft mission, said first evolution spacecraft being a deorbit propulsion module, said step of designing a first spacecraft including the steps of:designing a first outer spacecraft housing, said first spacecraft housing including a housing cylinder and a housing end wall;designing an internal support structure within the first spacecraft housing, said internal support structure including a plurality of inner compartment wall members defining a plurality of compartments; anddesigning the orientation of a plurality of spacecraft components within the compartments in the first spacecraft housing, said step of designing the orientation of spacecraft components including the steps of establishing the position of at least one propellant tank within at least one of the compartments in the spacecraft housing and establishing the position of at least one avionics module within one of the compartments in the spacecraft housing; anddesigning a second evolution spacecraft based on the first evolution spacecraft for another spacecraft mission, said second evolution spacecraft being a crew transfer vehicle, said step of designing a second evolution spacecraft including using the internal support structure and including redesigning the orientation of spacecraft components by adding, exchanging and/or repositioning spacecraft components, wherein the other spacecraft mission is a different mission type and requires significant design differences and mission goals than the one spacecraft mission.
이 특허에 인용된 특허 (2)
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Gschel Wilhelm (Taufkirchen DEX), Method and apparatus for controlling a satellite.
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Rourke Kenneth H. (Palos Verdes Estates CA) Hart Raymond J. (Villa Park CA), Multipurpose modular spacecraft.
이 특허를 인용한 특허 (9)
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Behrens, John W.; Chandler, Frank O.; Cronick, Jeffrey J., Exchangeable propellant cartridge system.
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Kistler, Walter P.; Taylor, Thomas C.; Citron, Robert A., Large cryogenic tank logistics for in-space vehicles.
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Bigelow,Robert, Method for assemblying and landing a habitable structure on an extraterrestrial body.
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Aston, Richard W.; Tomzynska, Anna M.; Langmack, Michael J.; Peterka, III, James J., Modular core structure for dual-manifest spacecraft launch.
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Kistler,Walter P.; Citron,Robert A.; Taylor,Thomas C., Platform and system for mass storage and transfer in space.
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Kistler,Walter P; Citron,Robert A; Taylor,Thomas C, Platform and system for mass storage and transfer in space.
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Behrens, John W.; Chandler, Frank O.; Cronick, Jeffrey J., Space depot for spacecraft resupply.
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Kistler,Walter P.; Citron,Robert A.; Taylor,Thomas C., System and method for transportation and storage of cargo in space.
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Izumiyama, Taku; Mori, Hatsuo; Hashimoto, Kozue; Nagao, Toru, Vapor jetting device and spacecraft.
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