[특허]Spacecraft with a crew escape system

[미국특허] Spacecraft with a crew escape system 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-037/02
출원번호	US-0256295 (1994-06-29)
우선권정보	RU-0003493 (1992-11-03)
국제출원번호	PCT/RU93/00184 (1993-08-04)
§371/§102 date	19940629 (19940629)
국제공개번호	WO-9410035 (1994-03-11)
발명자 / 주소	Meston Vyacheslav A. (Altufievskoe Shosse d.86 kv. 275 Moscow RUX 127349)
인용정보	피인용 횟수 : 36 인용 특허 : 0

초록 ▼

The spacecraft comprises a fuselage (1), a wing (2), a power unit incorporating two liquid-propellant launching rocket engines (3), two liquid-propellant boost rocket engines (4), six transverse-thrust rocket engines (5) located in the spacecraft fuselage (1) on a rotatable ring (6), solid-propellant emergency deceleration rocket engines (7), and solid-propellant additional boosting rocket engines (8), a payload compartment (9), a crew compartment (10), a tail unit with two vertical fin struts (11) a bottom tailplane (12), and a top tailplane (13). The fuselage (1) is provided with a movable center conical body (14). The spacecraft landing gear has a swivelling tail wheel (21). The crew compartment (10) is interposed between the fin struts (11) under the top tailplane (13). The spacecraft is provided with an orbital maneuvering system whose final control elements are in fact low-thrust rocket engines (22) and (23), and gyrodynes. The crew escape system comprises an escape module (24) which is in fact a recoverable ballistic capsule held to the end face of the tail portion of the fuselage (1). The capsule (24) communicates with the crew compartment (10) through a tunnel (25) provided with means for crew transfer from the crew compartment (10) to the capsule (24). The capsule (24) has a front and a rear hatch, an aerodynamic decelerator, and a parachute system. The front portion of the capsule (24) has a heat-protective coating (36). The center of mass of the capsule is displaced towards its front portion.

대표청구항 ▼

A spacecraft being a single-stage aerospace vehicle comprising: a fuselage provided with a crew compartment; a payload compartment; a center conical body located in a nose portion of the fuselage; the center conical body is mounted movable along a vehicle fore-and-aft axis and has a power actuator; a landing gear, incorporating a multiwheel bogey and a nose wheel; a variable-sweep wing; a power plant; an orbital maneuvering system provided with actuators; a crew escape system provided with an escape module (24); the escape module of the crew escape system is located on an end face of a tail portion of the vehicle fuselage; wherein the power plant comprises two launching rocket engines and two boost rocket engines mounted pairwise on the outer wing panels symmetrically with respect to the vehicle fore-and-aft axis, two solid-propellant additional boosting rocket engines, and two solid-propellant emergency deceleration rocket engines arranged pairwise in a common casing with their nozzles facing opposite sides and located at the tips of the outer panels of the wing, six liquid-propellant transverse-thrust rocket engines located in the vehicle fuselage on a rotatable ring and spaced equidistantly along the ring periphery, the center of the ring coinciding with the center of mass of the vehicle; production doors are provided in the upper portion of the vehicle fuselage for installing the transverse-thrust engines, and an opening is made in the lower portion of the fuselage for the exhaust gases of the transverse-thrust engines to escape, said opening being provided with extensible sliding shutters and flame deflectors; said vehicle a tail portion comprising two spaced-apart fin struts, and a horizontal tail consisting of two parallel tailplanes, being a top tailplane and a bottom tailplane, the bottom tailplane is a variable-sweep and is held to the vehicle fuselage, while the top tailplane is displaced with respect to the bottom tailplane towards the tail portion of the fuselage and is held to the ends of the fin struts; said crew compartment is interposed between the fin struts under the top tailplane; said actuators of the orbital maneuvering system are low-thrust rocket engines located at the tips of the tailplanes, and power assisted gyro stabilizers mounted in the fin struts and at the tips of the outer panels of the wing. A crew escape system according to claim 5, wherein the aerodynamic decelerator of the capsule is in fact a number of spring-loaded strips hinge-joined to the casing of the capsule and adjoining the capsule when in folded position, being kept in said position by the jettisonable cowling, the strips being provided with retainers of their expanded position.

이 특허를 인용한 특허 (36) 인용/피인용 타임라인 분석

Gall, Pierre-Emmanuel; Ricouard, Julien, Aircraft.
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Talmage, Jr., Robert N., Aircraft escape cabin.
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Al-Sabah Sabah Naser,KWX, Aircraft having raised and rearward positioned cockpit.
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Sankrithi Mithra M. K. V. ; Kyle Marlyn E., Aircraft lower lobe sleeping compartment.
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Cazals, Olivier, Aircraft tail.
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Cazals, Olivier, Aircraft tail.
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Gall, Pierre-Emmanuel; Ricouard, Julien, Aircraft tail.
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Morgenstern,John M.; Arslan,Alan E., Aircraft thickness/camber control device for low sonic boom.
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Featherstone, Mark; Boelitz, Frederick W.; Ramsey, Roger E.; Biggs, David M., Control surfaces for use with high speed vehicles, and associated systems and methods.
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Wentland Mark E. ; Oakes Gregory J., Escape systems for aircraft overhead rest areas.
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Towne,Andrew James, High wing monoplane aerospace plane based fighter.
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Nakagawa, Shingo; Fukui, Atsushi, Hydraulic apparatus for aircraft actuators.
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Luther, David I., In-line staged horizontal takeoff and landing space plane.
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Luther, David, In-line staged horizontal takeoff vehicles and related methods.
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Snowhook David P., Integrated launch and spacecraft propulsion system.
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Conners, Timothy R.; Henne, Preston A.; Howe, Donald C., Isentropic compression inlet for supersonic aircraft.
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Conners, Timothy R.; Howe, Donald C.; Henne, Preston A., Isentropic compression inlet for supersonic aircraft.
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Henne, Preston A.; Conners, Timothy R.; Howe, Donald C., Isentropic compression inlet for supersonic aircraft.
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Henne, Preston A.; Conners, Timothy R.; Howe, Donald C., Isentropic compression inlet for supersonic aircraft.
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Morris, Dennis E.; Little, Alfred, Launch abort and orbital maneuver system.
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Featherstone, Mark; Sanders, John Michael; Ramsey, Roger E.; Wetzel, Eric David, Launch vehicles with ring-shaped external elements, and associated systems and methods.
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Conners, Timothy R., Low shock strength inlet.
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Conners, Timothy R., Low shock strength inlet.
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Conners, Timothy R., Low shock strength propulsion system.
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Conners, Timothy R., Low shock strength propulsion system.
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Corda,Stephen; Smith,Mark Stephen; Myre,David Daniel, Method for creating an aeronautic sound shield having gas distributors arranged on the engines, wings, and nose of an aircraft.
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Aldrin, Buzz, Multi-crew modules for space flight.
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Johnson,Michael D.; Baker,James D.; Eichstadt,Frank T.; Bain,Michael E., Multipurpose modular spacecraft.
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Im, Sunstar, Personal spacecraft.
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Bahn, Patrick R. E., Rocket stage and method of improving an existing rocket stage.
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Gineris, Michael Brian; Stewart, Aubrey Lee; Fieler, Christopher Howard, Self-closing access door.
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Henne, Preston A.; Conners, Timothy R.; Howe, Donald C., Supersonic aircraft jet engine installation.
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Simonov Mikhail P.,RUX ; Merkulov Viktor I.,RUX ; Ivanov Yury L.,RUX ; Marbashev Konstantin K.,RUX ; Maranov Aleksandr Y.,RUX ; Klyagin Anatoly S.,RUX ; Chernov Leonid G.,RUX, Supersonic aircraft with in-flight refueling system.
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Henne, Preston A.; Howe, Donald C., Supersonic aircraft with spike for controlling and reducing sonic boom.
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Henne, Preston A.; Howe, Donald C.; Wolz, Robert R.; Hancock, Jr., Jimmy L., Supersonic aircraft with spike for controlling and reducing sonic boom.
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Henne, Preston A.; Howe, Donald C.; Wolz, Robert R.; Hancock, Jr., Jimmy L., Supersonic aircraft with spike for controlling and reducing sonic boom.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Spacecraft with a crew escape system 원문보기