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1. 发明公开

EP2443413A4 MODULAR DIVERT AND ATTITUDE CONTROL SYSTEM 有权
标题翻译：模块化UMLENKUNGS- UND AUSRICHTUNGSSTEUERUNGSSYSTEM
公开(公告)号：EP2443413A4
公开(公告)日：2015-01-07
申请号：EP10790009
申请日：2010-06-14
申请人： RAYTHEON CO
发明人： OLDEN THOMAS A , CAVALLERI ROBERT J
IPC分类号： F42B10/66 , F02K9/26 , F42B15/00
CPC分类号： F42B15/01 , F02K9/18 , F02K9/26 , F05D2240/40 , F42B10/661

2. 发明公开

EP1960654A4 HYBRID ROCKET SYSTEM 有权
标题翻译：混合火箭系统
公开(公告)号：EP1960654A4
公开(公告)日：2009-10-28
申请号：EP06817596
申请日：2006-12-07
申请人： ROCKETONE AEROSPACE PTY LTD
发明人： HO SOOK YING
IPC分类号： F02K9/72 , F02K9/08 , F02K9/26 , F02K9/84
CPC分类号： F02K9/72 , F02K9/26 , F05D2270/051

3. 发明公开

EP1960654A1 HYBRID ROCKET SYSTEM 有权
标题翻译：混合火箭系统
公开(公告)号：EP1960654A1
公开(公告)日：2008-08-27
申请号：EP06817596.7
申请日：2006-12-07
申请人： Rocketone Aerospace Pty Ltd
发明人： HO, Sook, Ying
IPC分类号： F02K9/72 , F02K9/08 , F02K9/26 , F02K9/84
CPC分类号： F02K9/72 , F02K9/26 , F05D2270/051
摘要： The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant to the solid reactant in the combustion chamber. In this way it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust.

4. 发明公开

EP1153213A2 PROPELLANT GRAIN CAPABLE OF GENERATING BUFFERED BOUNDARY LAYER FOR REDUCING ROCKET NOZZLE RECESSION 有权
标题翻译：固体燃料组装置，用于产生AGAINST THE上穿火箭保护层流INTERNATIONAL
公开(公告)号：EP1153213A2
公开(公告)日：2001-11-14
申请号：EP00939274.7
申请日：2000-02-15
申请人： ALLIANT TECHSYSTEMS INC.
发明人： PATE, Robert, A. , PERKINS, Frederick, M.
IPC分类号： F02K9/12 , F02K9/26 , F02K9/62
CPC分类号： F02K9/26 , F02K9/12 , F02K9/28 , F02K9/62
摘要： This rocket motor propellant grain is designed to reduce recession of at least the converging portion of a converging/diverging rocket motor nozzle. The propellant grain has an oxidizer-deficient grain portion constructed and arranged in relation to the nozzle to create, upon ignition of the propellant, a boundary layer of oxygen-deficient combustion products that flows through the nozzle throat passage and over an internal surface region of the nozzle. The boundary layer functions to at least substantially isolate the internal surface region of the nozzle from oxidizers contained in the combustion products generated from portions of the propellant grain having higher concentrations of oxygen than the oxidizer-deficient grain portion. As a result, the oxygen-rich portions of the propellant are unable to react with and thereby cause recession of the nozzle internal surface.

5. 发明公开

EP1057996A2 Feststofftriebwerk für eine Staustrahlrakete 审中-公开
标题翻译： Feststofftriebwerkfüreine Staustrahlrakete
公开(公告)号：EP1057996A2
公开(公告)日：2000-12-06
申请号：EP00111216.8
申请日：2000-05-25
申请人： DaimlerChrysler AG
发明人： Engel, Herbert
IPC分类号： F02K9/34 , F02K7/18 , F02K9/26
CPC分类号： F02K9/34 , F02K7/18 , F02K9/26
摘要： Es wird ein Feststofftriebwerk für eine Staustrahlrakete beschrieben, das eine von einem röhrenförmigen Mantel (2) umhüllte Brennkammer (B) und einen der Brennkammer (B) vorgelagerten, von einem röhrenförmigen Mantel (1) umhüllten Gaserzeuger (G) zur Erzeugung eines Brenngases aus einem Festtreibstoff und eine zwischen Gaserzeuger (G) und Brennkammer (B) angeordnete Gasstromregeleinheit (R) zur Regelung des vom Gaserzeuger (G) der Brennkammer (B) zugeführten Brenngasstroms enthält. Erfindungsgemäß enthält das Triebwerk eine die Gasstromregeleinheit (R) beherbergende Mittelsektion (4), welche in einer lasttragenden Verbindung mit dem Brennkammermantel (2) und dem Gaserzeugermantel (1) angeordnet ist und einen den Gaserzeuger (G) abschließenden ersten Druckboden (8) und einen die Brennkammer (B) abschließenden zweiten Druckboden (9) und eine zwischen den Druckböden (8,9) angeordnete, die Gasstromregeleinheit (R) beherbergende und die Druckböden (8,9) abstützende Basisstruktur aufweist.
摘要翻译：发动机具有带有护套（2）的燃烧室（B），带护套（1）的气体发生器（G）和包含气体流量调节器（R）的具有护套（4a）的中心部分。中心部分包括通过密封元件（19,20）密封在气体发生器和燃烧室上的压力中性区域（Z）。测量和供应线路通过该区域进入基础结构内部（7）。压力中性区由发电机和燃烧室的压力基座（8,9）和护套结构限定。

6. 发明公开

EP0028150A1 Improvements in rocket motors or gas generators 失效
标题翻译：或火箭发动机，气体发生器。
公开(公告)号：EP0028150A1
公开(公告)日：1981-05-06
申请号：EP80303794.4
申请日：1980-10-24
申请人： MORTON THIOKOL, INC.
发明人： Whitesides, Roger H.Jr.
IPC分类号： F02K9/36 , F02K9/26 , F02K9/34
CPC分类号： F02K9/346 , F02K9/26 , F02K9/36
摘要： A solid propellant rocket motor or gas generator of the type having retractable filaments (18) embedded in the propellant (13) for the purpose of controlling the overall thrust or mass flow output is combined with a channeled separator (14) located between the propellant (13) and its casing (10) with the channels (16) open to the combustion chamber via ports (17). This results in distribution of combustion chamber pressure and temperatures over the exterior of the propellant grain (13) so that distortion of the grain will not occur sufficiently to cause binding or sticking of the filaments (18) in their holes in the propellant nor will the holes be enlarged to cause uncontrolled burning between the filament and the hole.

7. 发明授权

EP2443413B1 MODULAR DIVERT AND ATTITUDE CONTROL SYSTEM 有权
标题翻译：模块化的偏见和态度控制系统
公开(公告)号：EP2443413B1
公开(公告)日：2017-09-06
申请号：EP10790009.4
申请日：2010-06-14
申请人： Raytheon Company
发明人： OLDEN, Thomas A. , CAVALLERI, Robert J.
IPC分类号： F42B10/66 , F42B15/01 , F02K9/18 , F02K9/26
CPC分类号： F42B15/01 , F02K9/18 , F02K9/26 , F05D2240/40 , F42B10/661

8. 发明公开

EP2959150A2 ROCKET DELAY APPARATUSES, SYSTEMS AND METHODS 有权
标题翻译：火箭延迟器件，系统和方法
公开(公告)号：EP2959150A2
公开(公告)日：2015-12-30
申请号：EP14757693.8
申请日：2014-02-21
申请人： Rosenfield, Gary C.
发明人： Rosenfield, Gary C.
IPC分类号： F02K9/32
CPC分类号： F42C19/0815 , F02K9/10 , F02K9/26 , F02K9/32 , F02K9/95 , F42B15/10 , F42C19/0819
摘要： Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

9. 发明公开

EP2443413A1 MODULAR DIVERT AND ATTITUDE CONTROL SYSTEM 有权
标题翻译：模块化转向定向和控制系统
公开(公告)号：EP2443413A1
公开(公告)日：2012-04-25
申请号：EP10790009.4
申请日：2010-06-14
申请人： Raytheon Company
发明人： OLDEN, Thomas A. , CAVALLERI, Robert J.
IPC分类号： F42B15/00
CPC分类号： F42B15/01 , F02K9/18 , F02K9/26 , F05D2240/40 , F42B10/661
摘要： 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.

10. 发明授权

EP1960654B1 HYBRID ROCKET SYSTEM 有权
标题翻译： HYBRIDRAKETENSYSTEM
公开(公告)号：EP1960654B1
公开(公告)日：2011-09-14
申请号：EP06817596.7
申请日：2006-12-07
申请人： Rocketone Aerospace Pty Ltd
发明人： HO, Sook, Ying
IPC分类号： F02K9/72 , F02K9/08 , F02K9/26 , F02K9/84
CPC分类号： F02K9/72 , F02K9/26 , F05D2270/051
摘要： The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant to the solid reactant in the combustion chamber. In this way it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust.

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