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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 有权转让
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

EP2964947B1 DISPOSITIF DE MODULATION DE SECTION D'EJECTION DE GAZ 有权转让
公开(公告)号：EP2964947B1
公开(公告)日：2018-12-12
申请号：EP14718652.2
申请日：2014-03-04
申请人： ARIANEGROUP SAS
发明人： CLERMONT, Mathieu , REMIGI, Alain , LARRIEU, Jean-Michel , MARLIN, Philippe
IPC分类号： F02K9/86
CPC分类号： F02K9/86 , F02K9/08 , F02K9/26

8. 发明授权

EP2959150B1 ROCKET DELAY APPARATUSES, SYSTEMS AND METHODS 有权
公开(公告)号：EP2959150B1
公开(公告)日：2018-08-29
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： F42C19/08 , F02K9/10 , F02K9/95 , F02K9/26 , F42B15/10 , 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

EP2964947A1 DISPOSITIF DE MODULATION DE SECTION D'EJECTION DE GAZ 有权转让
标题翻译： DEVICE调制的气体排放SECTION
公开(公告)号：EP2964947A1
公开(公告)日：2016-01-13
申请号：EP14718652.2
申请日：2014-03-04
申请人： HERAKLES
发明人： CLERMONT, Mathieu , REMIGI, Alain , LARRIEU, Jean-Michel , MARLIN, Philippe
IPC分类号： F02K9/86
CPC分类号： F02K9/86 , F02K9/08 , F02K9/26
摘要： A device for modulating a gas ejection section (100) comprising a partial sealing member (111) for partially sealing a nozzle neck (13), a control guide (112) for controlling the sealing member (111), a main piston (120) and a priming piston (130). The control guide (112) is movable between a retracted position in which the partial sealing member (111) is retracted relative to the nozzle neck (13) and a sealing position in which the partial sealing member (111) is in contact with the nozzle neck (13). The priming piston (130) is movable between an idle position and a priming position of the main piston (120) when the pressure in the modulation device reaches a first predefined value. The main piston (120) is movable between a first locked position that locks the movement of the control guide (112) in the retracted position of same and a second locked position that locks the control guide (112) when the pressure in the modulation device reaches a second predefined value lower than the first predefined value.

10. 发明公开

EP2964946A1 TUYERE A SECTION DE COL VARIABLE DE PROPULSEUR D'ENGIN AEROSPATIAL MUNIE D'UN POINTEAU MOBILE 有权转让
标题翻译：中变截面颈部与移动针头的空间PUSH工作NOZZLE
公开(公告)号：EP2964946A1
公开(公告)日：2016-01-13
申请号：EP14718647.2
申请日：2014-03-04
申请人： HERAKLES
发明人： CLERMONT, Mathieu , SORGEON, Sylvain , LARRIEU, Jean-Michel
IPC分类号： F02K9/86 , F02K1/08 , F02K9/80
CPC分类号： F02K9/86 , F02K1/08 , F02K9/26 , F02K9/805
摘要： A nozzle having a variable neck section for a spacecraft thruster, comprising a cylindrical housing having a neck (30) of which the opening diameter is smaller than the diameter of the housing, and a needle (24) capable of sliding into the housing between a front position of high-flow operation in which a nose (28) is recessed relative to the neck of the housing and a back position of low-flow operation in which the nose is abutted against the neck, the needle comprising a rod (26) intended to slide into the housing in the nozzle, the rod ending with the nose having a decreasing diameter. The nose of the rod is capable of coming into abutment against the neck of the housing in the nozzle forming a seat, and comprises at least two axial grooves (34) provided on the outer periphery of same to allow gas to flow when the nose axially abuts against the neck of the housing in the nozzle.

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