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1. 发明公开

CN109339979A 姿控发动机模块有权
公开(公告)号：CN109339979A
公开(公告)日：2019-02-15
申请号：CN201810969059.X
申请日：2018-08-23
申请人：上海空间推进研究所
发明人：周明龙 , 叶超 , 任建军
IPC分类号： F02K9/44 , F02K9/58 , F02K9/60 , F02K9/76
CPC分类号： F02K9/44 , F02K9/58 , F02K9/60 , F02K9/766
摘要：本发明提供了一种姿控发动机模块，包含模块支架与发动机；所述模块支架内部设置有第一空腔，所述第一空腔形成流体供应流道；所述发动机上设置有第二空腔，所述第二空腔形成流体接收流道；模块支架与发送机紧固连接，使的流体供应流道与流体接收流道之间相互连通并共同形成流体通道；流体供应流道与流体接收流道连接处设置有密封结构。本发明在实际应用中，模块支架通过内部打孔可形成4条氧化剂流道和4条燃料流道，工艺技术成熟、力学性能好，比传统设计减少了8根管路和16条焊缝，系统复杂程度降低。

2. 发明授权

US06499696B1 Rocket engine with reduced thrust and stagable venting system 有权
标题翻译：火箭发动机具有减小的推力和不稳定的排气系统
公开(公告)号：US06499696B1
公开(公告)日：2002-12-31
申请号：US09810850
申请日：2001-03-16
申请人： Martin R. Malinowski
发明人： Martin R. Malinowski
IPC分类号： B64G900
CPC分类号： B64G1/401 , B64G1/002 , F02K9/566 , F02K9/60 , F02K9/766 , F02K9/94
摘要： A rocket having a rocket engine vent system for a rocket engine is disclosed. The rocket engine vent system includes at least one rocket engine vent system conduit having a pair of vent apertures that are disposed on opposite sides of this conduit (i.e., disposed in opposing relation). A diverter with a pair of vanes is disposed within this rocket engine vent system conduit. One diverter vane projects toward one of the vent apertures, while the other diverter vane projects toward the other vent aperture. Two separate and discrete fluid flows are thereby directed out of the rocket engine vent system conduit in at least generally opposite directions, which significantly reduces the thrust to which the rocket engine is exposed when venting rocket fuel therefrom under high pressure conditions.
摘要翻译：公开了一种具有用于火箭发动机的火箭发动机排放系统的火箭。火箭发动机排气系统包括至少一个火箭发动机排气系统管道，其具有设置在该导管的相对侧上的一对通气孔（即以相对关系设置）。具有一对叶片的转向器设置在该火箭发动机排气系统管道内。一个分流叶片朝向一个通气孔突出，而另一个转向叶片向另一个通气孔突出。因此，两个分离的和离散的流体流动以至少大体上相反的方向被引导出火箭发动机排气系统管道，这显着地降低了在高压条件下从其中排出火箭燃料时火箭发动机暴露的推力。

3. 发明授权

US3173250A Reverse flow thrust chamber 失效
标题翻译：逆流推力室
公开(公告)号：US3173250A
公开(公告)日：1965-03-16
申请号：US2712660
申请日：1960-05-05
申请人： NORTH AMERICAN AVIATION INC
发明人： MATZENAUER JAMES O
IPC分类号： F02K9/62 , F02K9/76 , F02K9/97
CPC分类号： F02K9/766 , F02K9/62 , F02K9/97

4. 发明授权

US3034293A Booster and sustainer thrust devices 失效
标题翻译：增压器和支撑推力装置
公开(公告)号：US3034293A
公开(公告)日：1962-05-15
申请号：US80455559
申请日：1959-04-06
申请人： FERRIS DE LACY F , ROBERTSON YOUNGQUIST
发明人： FERRIS DE LACY F , ROBERTSON YOUNGQUIST
IPC分类号： F02K9/76
CPC分类号： F02K9/766 , Y10T137/1624

5. 发明授权

EP4278080B1 AEROSPIKE ENGINES, LAUNCH VEHICLES INCORPORATING SUCH ENGINES AND METHODS 有权
公开(公告)号：EP4278080B1
公开(公告)日：2024-09-11
申请号：EP22700386.0
申请日：2022-01-11
IPC分类号： F02K9/97 , F02K9/64 , F02K9/76
CPC分类号： F02K9/97 , F02K9/64 , F02K9/766 , F05D2230/3020130101 , F05D2260/20820130101 , F05D2300/17220130101

6. 发明公开

EP2393714A1 Réservoir cryogénique et lanceur supatial comportant un tel réservoir 有权
标题翻译：低温储罐和运载火箭这样的TANK
公开(公告)号：EP2393714A1
公开(公告)日：2011-12-14
申请号：EP10707603.6
申请日：2010-01-28
申请人： L'Air Liquide Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude
发明人： LACAPERE, Jérôme , BUTTERWORTH, James
IPC分类号： B64G1/40 , F17C13/00
CPC分类号： B64G1/402 , B65D88/12 , F02K9/766 , F17C13/088 , F17C2223/0161 , F17C2270/0194 , Y10T137/86212 , Y10T137/86348
摘要： The invention relates to a cryogenic tank for a space launcher, including a partition (2) defining upper (VS) and lower (VI) spaces for the fluid in the tank, said upper and lower spaces communicating via at least one free central opening (3) formed in the partition so as to enable a flow of the liquid from the upper space to the lower space by gravity and via the central opening(s) and so as to prevent the backflow of fluid from the lower space to the upper space via said central opening(s) due to acceleration forces, the tank further including at least one vent (5) separate from the central opening(s) and ensuring the fluid communication between the upper and lower spaces, the vent being shaped so as to facilitate the transit of vapour from the lower space to the upper space and for preventing a liquid backflow from the lower space to the upper space.

8. 发明公开

EP1167188A4 METHOD FOR PLACING A PAYLOAD INTO ORBIT BY MEANS OF A HYBRID MULTIFUNCTION BOOSTER ROCKET EQUIPPED WITH A LIQUID-FUEL ROCKET PROPULSION SYSTEM (LRPS), HYBRID MULTIFUNCTION BOOSTER ROCKET WITH CRUISING LRPS AND DEVELOPMENT TEST THEREFOR 有权
标题翻译：程序的有效载荷送入轨道，使由混合手段和多功能，配备运载火箭，混合液体燃料火箭驱动系统与多功能与液体燃料火箭驱动系统搭载车辆和火箭THEREOF预期性能测试
公开(公告)号：EP1167188A4
公开(公告)日：2005-08-03
申请号：EP00970360
申请日：2000-10-13
申请人： FGUP G KOSM N PROIZV TS IM M V
发明人： KISELEV ANATOLY IVANOVICH , MEDVEDEV ALEXANDR ALEXEEVICH , KARRASK VLADIMIR KONSTANTINOVI , DERMICHEV GENNADY DMITRIEVICH , RADUGIN IGOR SERGEEVICH , PETROKOVSKY SERGEI ALEXANDROVI , MOTORNY EVGENY IVANOVICH , JURIEV VASILY JURIEVICH
IPC分类号： B64G1/00 , B64G1/24 , B64G1/40 , B64G1/64 , F01D11/24 , F02K9/76
CPC分类号： F02K9/766 , B64G1/002 , B64G1/007 , B64G1/242 , B64G1/401 , B64G1/402 , B64G1/404 , B64G1/641 , F01D11/24
摘要： The invention relates to a space-rocket technology and can be used for placing both a pilot-controlled and unpiloted space craft in the earth's orbit. The inventive method consists in igniting-up cruising liquid-fuel rocket engines (LRE) of all assembly units, when the propulsion power of LRE of the side units is set to maximum, and the LRE of the central unit is set relatively low. As far as a booster rocket accelerates the propulsion power of the LRE of the central unit is reduced up to 30% - 50% of the normal propulsion power and the propulsion power of the LRE of the side units is reduced in order to regulate inertial and aerodynamic characteristics of the rocket. The lower polyblocks unit of the booster rocket is built-up from identical blocks symmetrically arranged in sectors formed by swinging planes of the LRE. During the development test there exists an opportunity to preset identical weight-dimension characteristics and the propulsion power of the LRE of the lower assembly. Results of fly and ground tests are applicable for formatting the booster rockets of both a tandem and a hybrid scheme. The invention makes it possible to enlarge an acceptable range for changing the mass of payloads placed by the booster rockets on the orbit without incurring expenditure.

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