-
公开(公告)号：EP0666612B1
公开(公告)日：2001-10-24
申请号：EP94120944.7
申请日：1994-12-30
发明人： Robinson, Anthony D.
CPC分类号： B64G1/66 , B64G1/22 , B64G9/00 , H01Q1/288 , H01Q11/086 , Y10T16/5253
-
公开(公告)号：EP0640524B1
公开(公告)日：1999-10-13
申请号：EP94112788.8
申请日：1994-08-16
发明人： Frazier, Scott R.
IPC分类号： B64G1/10
-
公开(公告)号：EP0596400B1
公开(公告)日：1998-12-30
申请号：EP93117444.5
申请日：1993-10-27
发明人： Harris, Gary N.
IPC分类号： F42B15/38
CPC分类号： B64G1/641 , B64G1/645 , F42B15/38 , Y10T29/4998 , Y10T403/11
-
公开(公告)号：EP0640524A1
公开(公告)日：1995-03-01
申请号：EP94112788.8
申请日：1994-08-16
发明人： Frazier, Scott R.
IPC分类号： B64G1/10
摘要： The present invention comprises a method for injecting a heavier payload into orbit than is possible using a traditional method and the same rocket booster launch vehicle. The method of the present invention does not utilize a parking orbit and does not perform orbital injection at perigee or apogee of the desired orbit. Rather, in the present method the flight path angle is positive at the final lower stage booster burn so as to boost the perigee kick motor and payload into a suborbital trajectory (36) having a low perigee, which may be below the surface of the Earth (8). In the preferred embodiment, the launch vehicle maintains a negative flight path angle during the PKM burn. The PKM burn does not occur at perigee, but perigee is at the desired location when the PKM burn is complete. Use of this method increases the payload capacity of some launch vehicles by up to fifty percent (50%).
摘要翻译： 本发明包括一种使用传统方法和相同的火箭助推器运载火箭将较重的有效载荷注入轨道的方法。 本发明的方法不利用停车轨道，并且不在所需轨道的近地点或远地点进行轨道射流。 相反，在本方法中，在最后的较低级助燃器燃烧时，飞行路径角度为正，以便将近地点踢脚马达和有效载荷提升为具有低近地点的眶下轨迹（36），其可能在地球表面以下 （8）。 在优选实施例中，运载火箭在PKM燃烧期间保持负飞行路径角。 PKM烧伤不会在近地点发生，但是当PKM燃烧完成时，近地点位于所需的位置。 使用这种方法将一些运载火箭的有效负载能力提高了百分之五十（50％）。
-
5.发明公开ROCKET-POWERED, AIR-DEPLOYED, LIFT-ASSISTED BOOSTER VEHICLE FOR ORBITAL, SUPRAORBITAL AND SUBORBITAL FLIGHT 失效火箭驱动下，眶内，SUPRA轨道和亚轨道飞行的AIR EXTENDED，BOOST辅助航天器。
公开(公告)号：EP0364569A1
公开(公告)日：1990-04-25
申请号：EP89904991.0
申请日：1989-03-08
发明人： ELIAS, Antonio, Luis
摘要： Un lanceur à sustentation assistée propulsé par fusée et déployé en l'air (sigle anglais ALBV) (100) transporte efficacement des charges marchandes réduites à des altitudes et des vitesses orbitales, supraorbitales et suborbitales. L'ALBV est porté sous un avion de transport conventionnel (200) d'où il est largué à l'altitude et à la vitesse de lancement, ce qui apporte une énergie totale singificative à la trajectoire d'ascension de l'ALBV. L'ALBV comprend des ailes (23) de sustentation aérodynamique qui aident l'ascension du véhicule et des empennages de queue (24) qui commandent l'assiette pendant que le véhicule est dans l'atmosphère sensible. Après le lancement par larguage, une manoeuvre nouvelle en "S vertical" est effectuée par commande aérodynamique, provoquant l'ascension de l'ALBV (100) sur une trajectoire presque théoriquement optimale. Dans le mode préférentiel de réalisation, les ailes (23) et les empennages de queue (24) sont largués lorsque le véhicule quitte l'atmosphère sensible et que la sustentation aérodynamique prend fin. L'invention représente une amélioration frappante par rapport aux approches antérieures du lancement de charges marrchandes en orbite, étant donné qu'elle permet de pratiquement doubler la charge marchande utile qui peut être transportée par le lanceur par rapport à des véhicules identiques lancés du sol.
-
6.发明公开EMERGENCY COMMUNICATIONS CHANNEL SYSTEMS AND METHODS FOR SATELLITE COMMAND 有权系统及方法NOTKOMMUNIKATIONSKANAL的卫星COMMAND
公开(公告)号：EP2694374A2
公开(公告)日：2014-02-12
申请号：EP12714481.4
申请日：2012-04-04
发明人： BOILEAU, Steven, I. , VORIS, Bruce, Pressley , KEARNEY, Christopher, Owen , SCHAEFFER, Michael, Lee
CPC分类号： H04B7/18519 , H04B7/18569 , H04B7/18597
摘要： Systems and methods for commanding a satellite are provided. A system for commanding a satellite includes a data bus and a payload coupled to the data bus, the payload including a payload receiver. The system further includes a primary receiver coupled to the data bus and a processor coupled to the data bus. The processor configured to receive a first command from the primary receiver via the data bus, and to receive telemetry data from the payload via the data bus. The processor is further configured to detect a second command by processing the telemetry data received from the payload, and to execute the detected second command.
-
公开(公告)号：EP0669251A2
公开(公告)日：1995-08-30
申请号：EP94120968.6
申请日：1994-12-30
CPC分类号： B64G1/641 , B64G1/002 , B64G1/1007 , B64G1/1085 , B64G1/222 , B64G1/44 , B64G1/645 , B64G2001/643 , Y10S136/292
摘要： A satellite (10) has two solar array panels (40,42) which are moveable between a closed configuration and an open configuration. The solar array panels are pivotably mounted on hinges (44,46) attached along the top and bottom of the satellite and extend outwardly from the top and bottom of the satellite in the open configuration. The height of the perimeter sidewall (14) is selected such that the satellite has a generally oblate configuration. Each solar array panel has a surface area substantially equal to that of the satellite cross-sectional area. The hinges (44,46) are mounted on pintles (48,50) extending from a solar array drive motor (58) which rotates the solar panel about the axis defined by the pintles to provide one axis sun tracking. The solar array panels are pivoted about the axes of the hinges until substantially parallel to the top and bottom of the satellite to form a compact, stackable configuration of the satellite for stowage. Three couplers (54A,54B,54C) positioned along the perimeter wall couple the satellite to similarly configured satellites within the fairing of a launch vehicle. The coupled satellites form a stack having three load-bearing columns consisting of the satellite couplers. In the stacked configuration, the couplers of one satellite are attached to the couplers of adjacent satellites by bolts restrained within non-explosive separation nuts (106). Pre-loaded compression springs (144A,144B) extend between the couplers of adjacent satellites. After the stack of satellites separates from the fairing (52), each satellite is successively deployed from the stack, starting with the top-most satellite. Deployment begins by activating the non-explosive separation nuts (106) in the couplers of the top-most satellite. Thereafter, the pre-loaded compression springs (144A,144B) extending between the coupling devices of the top-most satellite and the subjacent satellite (or, for the bottom-most satellite, the subjacent booster stage) accelerate the top-most satellite away from the stack and booster stage.
摘要翻译： 卫星（10）具有两个太阳能电池阵列面板（40,42），其能够在闭合构造和开放构造之间移动。 太阳能电池阵列面板可枢转地安装在沿卫星的顶部和底部连接的铰链（44,46）上，并且在打开配置下从卫星的顶部和底部向外延伸。 周边侧壁（14）的高度被选择为使得卫星具有大致扁平的构造。 每个太阳能电池阵列面板具有基本上等于卫星截面面积的表面积。 铰链（44,46）安装在从太阳能电池阵列驱动电动机（58）延伸的枢轴（48,50）上，该驱动电动机使太阳能电池板围绕由枢轴限定的轴线旋转，以提供一个轴线的太阳跟踪。 太阳能电池阵列面板围绕铰链的轴线枢转，直到基本平行于卫星的顶部和底部，以形成用于装载的卫星的紧凑的可堆叠配置。 沿着周边壁定位的三个耦合器（54A，54B，54C）将卫星耦合到运载火箭的整流罩内的类似配置的卫星。 耦合的卫星形成一个堆叠，其具有三个由卫星耦合器组成的承载柱。 在堆叠配置中，一颗卫星的耦合器通过限制在非爆炸性分离螺母（106）内的螺栓附接到相邻卫星的耦合器。 预加载的压缩弹簧（144A，144B）在相邻卫星的耦合器之间延伸。 在一堆卫星与整流罩（52）分离之后，每个卫星从最上面的卫星开始依次从堆叠部署。 通过激活最顶端卫星耦合器中的非爆炸性分离螺母（106）开始部署。 此后，在最上面的卫星和下面的卫星（或者对于最下面的卫星，下面的升压器级）的耦合装置之间延伸的预加载的压缩弹簧（144A，144B）加速离开最上面的卫星 从堆叠和助推器阶段。
-
8.发明公开ROCKET-POWERED, AIR-DEPLOYED, LIFT-ASSISTED BOOSTER VEHICLE FOR ORBITAL, SUPRAORBITAL AND SUBORBITAL FLIGHT 失效枢纽动力，空中配备，起重机辅助起重机车辆，用于直升机，副驾驶和副驾驶
-
公开(公告)号：EP2973861A1
公开(公告)日：2016-01-20
申请号：EP14711404.5
申请日：2014-03-04
CPC分类号： H01Q3/20 , H01Q15/147 , H01Q15/165 , H01Q15/167
摘要： Systems and methods are disclosed herein for a reconfigurable faceted reflector for producing a plurality of antenna patterns. The reconfigurable reflector includes a backing structure, a plurality of adjusting mechanisms mounted to the backing structure, and a plurality of reflector facets. Each of the plurality of reflector facets is coupled to a respective one of the plurality of adjusting mechanisms for adjusting the position of the reflector facet with which it is coupled. The reflector facets are arranged to produce a first antenna pattern of the plurality of antenna patterns. By adjusting the plurality of adjusting mechanisms, the position of each of the reflector facets coupled to the respective one of the plurality of adjusting mechanisms is adjusted so that the reflector facets are arranged to produce a second antenna pattern of the plurality of antenna patterns.
-
公开(公告)号：EP2971740A1
公开(公告)日：2016-01-20
申请号：EP14721125.4
申请日：2014-03-14
发明人： ELIAS, Antonio, L.
IPC分类号： F02K9/48
摘要： Systems and methods are described herein for a hybrid liquid propellant rocket engine. In an embodiment, the engine includes a first pump powered by a first turbine, a second pump powered by a second turbine, and a gas generator. An output of the gas generator is connected to the first turbine and the second turbine. The engine further includes a third pump powered by a third turbine, a fourth pump powered by a fourth turbine, and a nozzle having an expander cycle in a wall and a combustion chamber. An output of the third pump is connected to the expander cycle and an output of the wall is connected to the third turbine and the fourth turbine. An output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.
-
-
-
-
-
-
-
-
-
搜索结果
28 条记录 (耗时 0.01 秒)
