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1. 发明申请

WO2012116398A1 ENGINE FOR USE IN AN AERIAL VEHICLE 审中-公开
标题翻译：发动机用于航空汽车
公开(公告)号：WO2012116398A1
公开(公告)日：2012-09-07
申请号：PCT/AU2012/000195
申请日：2012-02-29
申请人： GROLLO AEROSPACE , GROLLO, Mark
发明人： GROLLO, Mark
IPC分类号： F02K7/18 , F02K9/76 , F02K9/78
CPC分类号： F02K7/18 , F02K1/1223 , F02K9/78 , F02K9/86 , F02K9/972
摘要： This invention relates to an engine (2) for use in aerial vehicle (1) including a rocket (9) and ram jet engine formed from an intake (8) and a combustion chamber (10). The rocket engine (9) includes an oxidiser combustion chamber (21) which exhausts through the combustion chamber (10). The engine also includes a nozzle (12). Both the intake (8) and nozzle (12) include rectilinear ducts which are defined in part by baffles (16) and panels (33) respectively. Both the baffles (16) and panels (33) are adjustable to adjust the airflow characteristics therethrough.
摘要翻译：本发明涉及一种用于飞行器（1）的发动机（2），其包括由进气口（8）和燃烧室（10）形成的火箭（9）和冲程喷气发动机。火箭发动机（9）包括通过燃烧室（10）排出的氧化剂燃烧室（21）。发动机还包括喷嘴（12）。进气口（8）和喷嘴（12）都包括分别由挡板（16）和面板（33）部分限定的直线导管。挡板（16）和面板（33）都是可调节的，以调节通过其的气流特性。

2. 发明申请

WO2004038208A3 METHOD AND APPARATUS FOR THRUST VECTORING A FLIGHT VEHICLE USING A MULTI-PULSE ROCKET MOTOR 审中-公开
标题翻译：使用多脉冲电动机对飞行器进行转向的方法和装置
公开(公告)号：WO2004038208A3
公开(公告)日：2004-10-28
申请号：PCT/US0309656
申请日：2003-03-31
申请人： LOCKHEED CORP
发明人： BROWN CHARLES C , BEYER PHILIP T
IPC分类号： F02K9/28 , F02K9/42 , F02K9/80 , F02K9/94 , F42B10/64 , F42B10/66 , F42B15/01 , F02K9/76 , F02K9/90
CPC分类号： F42B10/66 , F02K9/28 , F02K9/42 , F02K9/80 , F02K9/94 , F42B10/64 , F42B15/01
摘要： A method and apparatus for thrust vectoring a flight vehicle (200) during homing are disclosed. The flight vehicle (200) includes a body (205); a plurality of attitude control mechanisms (215) on the body; a multi-pulse motor (230) housed at least partially in the body; and a control unit (225) housed in the body (205). The control unit (225) generates signals controlling an actuation of the attitude control mechanisms (215) and the multi-pulse motor (230) to initiate a follow-on burn of the multi-pulse motor (230) to effect a maneuver directed by the actuation of the attitude control mechanisms (215). The method includes conserving a second burn of a dual pulse motor (230) until target acquisition; acquiring a target; actuating a attitude control mechanism (215) for the flight vehicle (200) to alter the flight vehicle's heading; and initiating the second burn.
摘要翻译：公开了一种用于在归位期间对飞行器（200）进行推力矢量化的方法和装置。飞行器（200）包括主体（205）; 身体上的多个姿态控制机构（215）; 多个脉冲电机（230），其至少部分地容纳在所述主体中; 和容纳在主体（205）中的控制单元（225）。控制单元（225）产生控制姿态控制机构（215）和多脉冲马达（230）的致动的信号，以启动多脉冲马达（230）的后续燃烧，以进行由姿态控制机构（215）的致动。该方法包括保存双脉冲电动机（230）的第二次燃烧，直到目标获取; 获取目标; 启动用于所述飞行器（200）的姿态控制机构（215）以改变所述飞行器的航向; 并启动第二次烧伤。

3. 发明申请

WO2016055722A1 TUYERE D'ENGIN SPATIAL COMPRENANT UN SYSTEME DE DEPLOIEMENT AMELIORE 审中-公开
标题翻译：包括改进部署系统的SPACECRAFT喷嘴
公开(公告)号：WO2016055722A1
公开(公告)日：2016-04-14
申请号：PCT/FR2015/052637
申请日：2015-10-02
申请人： SNECMA
发明人： GAZAVE, Robert , MILLON, Frédérick , LELONG, Jacques
IPC分类号： F02K9/76 , F02K9/78
CPC分类号： F02K9/976 , B64G1/40 , F02K9/76 , F02K9/78 , F05D2220/80 , F15B1/02 , F15B11/20 , F15B15/20
摘要： Tuyère (1) d'un moteur (M) d'engin spatial, comprenant une portion fixe (2) et une portion mobile (3) la tuyère (1) comprenant un système de déploiement (4) pneumatique comprenant : - un vérin de déploiement (5), déployer la portion mobile (3) de la tuyère (1), - un vérin de déverrouillage haut (6), - un vérin de déverrouillage bas (7), - un éjecteur (41) le système de déploiement (4) comprenant un système d'alimentation (8) configuré de manière à, séquentiellement : - déplacer vérin de déploiement (5) de sa position de support vers sa position de déploiement; - déplacer les vérins de déverrouillage haut (6) et bas (7) dans leurs positions de déverrouillage haut et bas; - actionner l'éjecteur de manière à éjecter le système de déploiement (4) hors de la tuyère (1).
摘要翻译：包括固定部分（2）和移动部分（3）的航空发动机（M）的喷嘴（1），所述喷嘴（1）包括气动展开系统（4），所述气动展开系统包括： - 展开气缸（5）展开喷嘴（1）的移动部分（3）， - 上解锁缸（6），下解锁缸（7）和喷射器（41），所述展开系统（4）包括电源系统（8）被构造成顺序地： - 将展开气缸（5）从其支撑位置移动到其上的展开位置; - 将上部（6）和下部（7）解锁缸移动到其上部和下部解锁位置; - 并且以这样的方式激活喷射器，以将展开系统（4）从喷嘴（1）中排出。

4. 发明申请

WO0236955A8 METHOD AND DEVICE FOR A MULTIPLE STEP ROCKET 审中-公开
标题翻译：用于多个步骤的方法和装置
公开(公告)号：WO0236955A8
公开(公告)日：2005-11-10
申请号：PCT/SE0102381
申请日：2001-10-30
申请人： SAAB AB , NILSSON LARS , AX LARS
发明人： NILSSON LARS , AX LARS
IPC分类号： F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/95 , F02K9/97 , F42B15/36
CPC分类号： F42B15/36 , F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/763 , F02K9/95 , F02K9/978
摘要： The present invention relates to a method and an arrangement for, in multi-stage rockets (3) provided with a number of successively ignitable rocket engines (7, 13) arranged one in front of another in the flying direction of the rocket and joined together detachably with one another, each following rocket engine (13) in the ignition sequence depending, for its ignition, on being initiated after a preceding rocket engine (7) has been able to bun out, causing each preceding rocket engine (7) included in the ignition sequence to be jettisoned by virtue of the next engine having reached its working pressure. According to the invention, each preceding rocket engine is designed with a preferably conical guide part (11) which is directed forwards in the flying direction of the rocket and geometrically adapted to the exhaust nozzle (12) of the following rocket engine (13) and which, in the initial position, is fitted into said exhaust nozzle (12) and fixed in this position by means of at least one blocking part (15) which is deformable or capable of elastic recovery.
摘要翻译：本发明涉及一种多级火箭（3）中的方法和装置，该多级火箭（3）具有在火箭的飞行方向上一个在另一个前方排列并连接在一起的若干连续可点燃的火箭发动机（7,13）每个随后的火箭发动机（13）在点火顺序中依赖于其点火，在先前的火箭发动机（7）能够蹦出之后被启动，使得每个先前的火箭发动机（7）包括在由于下一个发动机已经达到其工作压力而要排出的点火顺序。根据本发明，每个先前的火箭发动机被设计成具有优选的圆锥形引导部分（11），其沿着火箭的飞行方向向前指向并几何地适应于随后的火箭发动机（13）的排气喷嘴（12）和其在初始位置被装配到所述排气喷嘴（12）中并且通过至少一个可变形或能够弹性恢复的阻挡部分（15）固定在该位置。

5. 发明申请

WO02036955A1 METHOD AND DEVICE FOR A MULTIPLE STEP ROCKET 审中-公开
标题翻译：用于多个步骤的方法和装置
公开(公告)号：WO02036955A1
公开(公告)日：2002-05-10
申请号：PCT/SE2001/002381
申请日：2001-10-30
IPC分类号： F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/95 , F02K9/97 , F42B15/36
CPC分类号： F42B15/36 , F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/763 , F02K9/95 , F02K9/978
摘要： The present invention relates to a method and an arrangement for, in multi-stage rockets (3) provided with a number of successively ignitable rocket engines (7, 13) arranged one in front of another in the flying direction of the rocket and joined together detachably with one another, each following rocket engine (13) in the ignition sequence depending, for its ignition, on being initiated after a preceding rocket engine (7) has been able to bun out, causing each preceding rocket engine (7) included in the ignition sequence to be jettisoned by virtue of the next engine having reached its working pressure. According to the invention, each preceding rocket engine is designed with a preferably conical guide part (11) which is directed forwards in the flying direction of the rocket and geometrically adapted to the exhaust nozzle (12) of the following rocket engine (13) and which, in the initial position, is fitted into said exhaust nozzle (12) and fixed in this position by means of at least one blocking part (15) which is deformable or capable of elastic recovery.
摘要翻译：本发明涉及一种多级火箭（3）中的方法和装置，该多级火箭（3）具有在火箭的飞行方向上一个在另一个前方排列并连接在一起的若干连续可点燃的火箭发动机（7,13）每个随后的火箭发动机（13）在点火顺序中依赖于其点火，在先前的火箭发动机（7）能够蹦出之后被启动，使得每个先前的火箭发动机（7）包括在由于下一个发动机已经达到其工作压力而要排出的点火顺序。根据本发明，每个先前的火箭发动机被设计成具有优选的圆锥形引导部分（11），其沿着火箭的飞行方向向前指向并几何地适应于随后的火箭发动机（13）的排气喷嘴（12）和其在初始位置被装配到所述排气喷嘴（12）中并且通过至少一个可变形或能够弹性恢复的阻挡部分（15）固定在该位置。

6. 发明申请

WO0034731A3 GAS GENERATING EJECT MOTOR 审中-公开
标题翻译：燃气发电机
公开(公告)号：WO0034731A3
公开(公告)日：2000-10-12
申请号：PCT/US9926455
申请日：1999-11-10
申请人： CORDANT TECH INC , DOLL DANIEL W , LUND GARY K , HUGHES CRAIG D , HALL MARC A , MACON DAVID J
发明人： DOLL DANIEL W , LUND GARY K , HUGHES CRAIG D , HALL MARC A , MACON DAVID J
IPC分类号： C06D5/06 , F02K9/10 , F02K9/36 , F02K9/76 , F02K9/95 , F42B3/04 , F42B5/10
CPC分类号： C06D5/06 , F02K9/10 , F02K9/36 , F02K9/763 , F02K9/95 , F42B3/04 , F42B5/105
摘要： A gas generating eject motor (10) includes a case (12) containing an ignitable low temperature gas generant material (24) that does not produce toxic gases upon the combustion thereof. The gas generant material is generally contained with a screen enclosure (26, 30) housed within the case. An igniter (70) is disposed within the gas generant material for selectively igniting the gas generant to thereby generate combustion gases. A nozzle (40) is disposed within an open aft end of the case for focusing and directing the combustion gases generated by the ignited gas generant material. The case is constructed and arranged to be separaly attached to the aft end of a rocket (90) to be launched from a launch platform (80), so that, upon ignition of the gas generant, the combustion gases focused by the nozzle will apply a thrust to the rocket and thereby propel, or eject, the rocket from the launch platform, at which time the combustible propellant of the rocket motor will ignite and the eject motor will be separated from the rocket.
摘要翻译：气体发生喷射电动机（10）包括容纳可燃低温气体发生剂材料（24）的壳体（12），其在其燃烧时不产生有毒气体。气体发生剂材料通常包含容纳在壳体内的筛网外壳（26,30）。点火器（70）设置在气体发生剂材料内，用于选择性地点燃气体发生剂从而产生燃烧气体。喷嘴（40）设置在壳体的开口后端，用于聚焦和引导由点燃气体发生剂材料产生的燃烧气体。壳体被构造和布置成分离连接到从发射平台（80）发射的火箭（90）的后端，使得当燃气发生器点燃时，由喷嘴聚焦的燃烧气体将应用推动火箭从而推动或弹出火箭从发射平台，此时火箭发动机的可燃推进剂将点燃，弹出电机将与火箭分离。

7. 发明申请

WO2022173709A1 EXPENDABLE MULTISTAGE PRESSURE-FED ABLATIVE-COOLING LOW TOXICITY LAUNCH VEHICLE 审中-公开
公开(公告)号：WO2022173709A1
公开(公告)日：2022-08-18
申请号：PCT/US2022/015551
申请日：2022-02-08
申请人： FAKAS, Sergii , CARPENTER, Michael , PARNOWSKI, Aleksei , GRECHULHIN, Mykhailo
发明人： CARPENTER, Michael , PARNOWSKI, Aleksei , GRECHULHIN, Mykhailo
IPC分类号： F02K9/97 , F02K9/42 , F02K9/46 , F02K9/50 , F02K9/60 , F02K9/64 , F02K9/76
摘要： An expendable launch vehicle is provided using pressure-fed liquid propellant fixed steering ablatively-cooled rocket engines. The vehicle is manufactured minimizing toxic or exotic metals and maximizing the use of conventional, inexpensive composites and 3D printed parts. Fuselage, fairing stage shells, adapters, propellant tanks, and even engine combustion chambers are unified for all stages, are ablatively cooled, and, like the fairing, integral propellant tanks and adapters, are made of composites or 3D printed parts. Using non-toxic materials with non-toxic by-products, and non-toxic fabrication methods, using mostly non-metallic components allows for an environmentally neutral design.

8. 发明申请

WO2022086587A1 MULTI-PULSE PROPULSION SYSTEM WITH PASSIVE INITIATION 审中-公开
公开(公告)号：WO2022086587A1
公开(公告)日：2022-04-28
申请号：PCT/US2021/017415
申请日：2021-02-10
申请人： RAYTHEON COMPANY
发明人： MCKNIGHT, Richard W. , HOMES, David W. , BURTCH, William
IPC分类号： F02K9/08 , F02K9/28 , F02K9/76 , F02K9/94 , F42B15/00
摘要： A multi-pulse propulsion system (10) includes at least one pulse chamber (20) containing at least one propellant (22) for igniting during at least one pulse of the multi-pulse propulsion system, at least one additional pulse chamber (24) containing at least one additional propellant (26) for igniting during at least one additional pulse of the multi-pulse propulsion system, and at least one passive fuzing system (34) configured to initiate the at least one additional pulse. The at least one passive fuzing system includes a sensor (36) and an igniter (38). The sensor is configured to sense an environmental condition and/or a ballistic condition. The igniter is configured to provide a stimulus that causes ignition of the at least one additional propellant in response to the sensor sensing that the environmental condition and/or the ballistic condition has reached or exceeded one or more threshold values.

9. 发明申请

WO01056880A1 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 审中-公开
标题翻译：通过装配有液体燃料轴向推进系统（LRPS）的混合多功能升降器摇杆将负载放置在轨道上的方法，具有检测LRPS和开发测试的混合多功能升降器
公开(公告)号：WO01056880A1
公开(公告)日：2001-08-09
申请号：PCT/RU2000/000406
申请日：2000-10-13
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.
摘要翻译：本发明涉及一种太空火箭技术，可用于将飞行员控制和无飞过的太空飞船放置在地球轨道上。当侧面单元的LRE的推进功率设定为最大，中央单元的LRE设置得相对较低时，本发明的方法包括点燃所有组装单元的液体燃料火箭发动机（LRE）。只要加速火箭加速，中央单元的LRE的推进力降低到正常推进力的30％-50％，并且侧部单元的LRE的推进力减小，以便调节惯性和火箭的空气动力特性。助推器火箭的下部多块单元由对称地布置在由LRE的摆动平面形成的扇区中的相同块构成。在开发测试期间，存在预设下部组件的LRE的相同重量尺寸特性和推进力的机会。飞行和地面测试的结果适用于格式化串联和混合方案的增压火箭。本发明可以扩大可变范围，以改变在轨道上由增压火箭放置的有效载荷的质量，而不产生支出。

10. 发明申请

WO00034731A2 GAS GENERATING EJECT MOTOR 审中-公开
标题翻译：排污发动机生产气体
公开(公告)号：WO00034731A2
公开(公告)日：2000-06-15
申请号：PCT/US1999/026455
申请日：1999-11-10
IPC分类号： C06D5/06 , F02K9/10 , F02K9/36 , F02K9/76 , F02K9/95 , F42B3/04 , F42B5/10 , F41A
CPC分类号： C06D5/06 , F02K9/10 , F02K9/36 , F02K9/763 , F02K9/95 , F42B3/04 , F42B5/105
摘要： A gas generating eject motor (10) includes a case (12) containing an ignitable low temperature gas generant material (24) that does not produce toxic gases upon the combustion thereof. The gas generant material is generally contained with a screen enclosure (26, 30) housed within the case. An igniter (70) is disposed within the gas generant material for selectively igniting the gas generant to thereby generate combustion gases. A nozzle (40) is disposed within an open aft end of the case for focusing and directing the combustion gases generated by the ignited gas generant material. The case is constructed and arranged to be separaly attached to the aft end of a rocket (90) to be launched from a launch platform (80), so that, upon ignition of the gas generant, the combustion gases focused by the nozzle will apply a thrust to the rocket and thereby propel, or eject, the rocket from the launch platform, at which time the combustible propellant of the rocket motor will ignite and the eject motor will be separated from the rocket.
摘要翻译：这种产生气体的排出发动机包括一个容纳低温易燃材料的容器，燃烧时产生无毒气体。这种材料通常包含在安置在胶囊内的屏幕外壳中。点火装置已被放置在材料中以选择性地点燃材料以产生燃烧气体。喷嘴安装在胶囊的敞开后端，以浓缩并引导由点燃材料产生的燃烧气体，从而产生气体。胶囊已被构造和布置成从发射平台可拆卸地连接到发射火箭的后端，并且在产生气体材料点燃时，由喷嘴集中的燃烧气体向火箭施加推力并且因此将其推进或从发射平台推出，此时火箭发动机的推进剂点亮并且发动机的发动机驱逐离开火箭。

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