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1. 发明公开

EP1162139A1 REUSABLE BOOSTER FOR THE FIRST STAGE OF A LAUNCHER 有权
标题翻译：威尼斯的ZUSATZRAKETEFÜRDIE ERSTE STUFE EINERTRÄGERRAKETE
公开(公告)号：EP1162139A1
公开(公告)日：2001-12-12
申请号：EP00970361.2
申请日：2000-10-13
申请人： Gosudarstvenny Kosmichesky Naucho-Proizvodstvenny Tsentr IM. M.V. Khrunicheva
发明人： KISELEV, Anatoly Ivanovich , MEDVEDEV, Alexandr Alexeevich , TRUFANOV, Jury Nikolaevich , RADUGIN, Igor Sergeevich , KUZNETSOV, Jury Leonidovich , PANKEVICH, Alexandr Alexandrovich , NABOISCHIKOV, Gennady Fedorovich , USHAKOV, Vladimir Mikhailovich
IPC分类号： B64G1/14 , F02K9/78
CPC分类号： F02K9/78 , B64G1/002 , B64G1/14 , B64G1/401
摘要： A booster comprises a body including tanks for an oxidizer and fuel, a nose compartment with a dome, a between-tank section and an afterbody, a rocket engine installation, an all-moving wing with a unit for turning it and fixing in a position along the axis of the booster during the ascension step and in a position turned by 90° during the return flight, horizontal and vertical fin assemblies, a triple-point support landing gear, aerodynamic control organs and units for jointing to the second stage of the launch vehicle. The booster is provided with an air-feed jet engine installation, comprising two engines with air intakes mounted in the nose compartment, and with gas-line extensions with exhaust nozzles extending beyond the bypasses of the external contours of the nose compartment, and a propellant system with propellant tanks in the wing, working and balancing tanks in the nose compartment. A wing is mounted on the upper surface of the booster body in the area of the between-tank section. Horizontal and vertical fins are mounted on the afterbody and are made respectively in the form of a stabilizer consisting of two all-moving consoles with a small negative V-shaped angle, and a fin with a yaw rudder. The dome of the nose compartment is made in the form of a portion of a sphere and has two inlet apertures for the aforesaid air intakes, closed by one turning plug. 6 dependent claims, 11 drawings.
摘要翻译：助推器包括一个主体，包括用于氧化剂和燃料的罐，具有圆顶的舱室，箱体间部分和后箱体之间的主体，火箭发动机装置，具有用于转动并固定在其上的单元的全动翼在升降步骤期间沿助力器的轴线，在返回飞行期间在90度的位置，水平和垂直翅片组件，三点支撑起落架，空气动力学控制机构和用于连接到第二阶段的单元运载火箭。增压器设置有空气进料喷射发动机装置，其包括两个引擎，其具有安装在鼻部隔室中的进气口，以及具有延伸超过鼻部隔室的外部轮廓的旁路的排气喷嘴的气体管线延伸部，以及推进剂在机翼中有推进剂罐的系统，鼻腔中的工作和平衡罐。机翼安装在助推器主体的上表面之间的槽间区域。水平和垂直翅片安装在后身上，并分别制成由两个具有小V形角度的全移动控制台组成的稳定器和具有偏航舵的翅片。鼻部隔室的圆顶以球体的一部分的形式制成，并且具有用于上述进气口的两个入口孔，由一个转动塞封闭。 6个从属权利要求，11个图纸。

2. 发明公开

EP1167188A1 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：程序的有效载荷在轨运行带来BY的混合多功能与液体燃料火箭驱动系统，配备运载火箭MEANS
公开(公告)号：EP1167188A1
公开(公告)日：2002-01-02
申请号：EP00970360.4
申请日：2000-10-13
申请人： Gosudarstvenny Kosmichesky Naucho-Proizvodstvenny Tsentr IM. M.V. Khrunicheva
发明人： KISELEV, Anatoly Ivanovich , MEDVEDEV, Alexandr Alexeevich , KARRASK, Vladimir Konstantinovich , DERMICHEV, Gennady Dmitrievich , RADUGIN, Igor Sergeevich , PETROKOVSKY, Sergei Alexandrovich , MOTORNY, Evgeny Ivanovich , JURIEV, Vasily Jurievich
IPC分类号： B64G1/00
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 the field of rocket-space engineering and may find application during the development of rocket-space systems serving to place manned and unmanned space ships into a near-earth orbit.
The method includes forming a launch assembly of a launch vehicle in accordance with a launch program, including a lower multiunit assembly of rocket units (RU), firing cruise LRESs of a central and side RUs at the launch, and operating the LRESs in accordance with the launch program. Identical RUs with adjustable LRESs of identical thrust are used to form the lower multiunit assembly. At the launch of the launch vehicle, LRESs of the side RUs have a nominal thrust, while the LRES of the central RU - a thrust equal to 90-100% of the nominal value. When the launch vehicle reaches a longitudinal acceleration of 12.7-16.7 m/sec 2 , the thrust of the LRES of the central RU is reduced to 0.3-0.5 of the nominal thrust until the LRESs of the side RUs are cut off. The reduction of the thrust of the LRESs of the side RUs is also presumed in order to adjust the inertial and aerodynamic loads on the launch vehicle.
The launch vehicle of a combined scheme comprises a lower multiunit assembly of RUs, composed of identical RUs, wherein the side RUs are mounted on the central RU symmetrically relative to its longitudinal axis in sectors formed by the swinging planes of the LRES of the central RU.
The method of refining the multifunctional launch vehicle presumes that during the selection of the characteristics of its RUs, identical size-mass characteristics and thrust of the LRESs of the lower multiunit assembly of RUs will be set, this ensuring use of the central RU in the makeup of a launch vehicle of a tandem scheme. The aforesaid RU is produced and its ground-based and flight-structural tests carried out, including in the makeup of a launch vehicle of a tandem scheme, and then it is used in the formation of a lower multiunit assembly of RUs of a launch vehicle of a combined scheme.
The main technical result from use of the invention is expansion of the range in which the payload being placed into orbit may change.
摘要翻译：本发明涉及火箭航天工程领域，可能会发现服务载人和无人飞船放置到近地轨道航天火箭系统的开发过程中的应用。该方法包括形成一个运载火箭在雅舞蹈发射组件具有发射方案，包括火箭单位（RU）的下多单元组件，在推出烧制的RU中央和侧的巡航LRESs，并在雅舞蹈与操作LRESs 启动程序。具有相同推力的可调LRESs相同RU被用来形成下多单元组件。在发射的运载火箭，侧RU的LRESs具有标称推力，而RU中央的LRES - 推力等于值标称的90-100％。当运载火箭达12.7-16.7米/秒<2>的纵向加速度，所述RU中央的LRES的推力降低到标称推力直到侧RU的LRESs 0.3-0.5被切断。该因此，RU的LRESs侧的推力的还原被假定以调整在发射车辆惯性和空气动力载荷。组合方案的运载火箭包括的RU的下多单元组件，worin侧的RU相同的RU组成被安装在中央RU对称相对于其纵向轴线上在由RU中央的LRES的摆动平面所形成的扇区，炼多功能运载火箭的方法假定的其RU的大小相同质量特性和RU的下多单元组件的所述LRESs的推力特性的选择期间那样将被设置，在此确保使用RU中央的串联方案的运载火箭的妆。上述RU产生和它的地基和飞行结构试验进行，包括在串联方式的运载火箭的化妆，然后将其在RU的运载火箭的下多单元组件的形成中使用的组合方案。从使用本发明的主要技术结果是在其中有效负载被放入轨道可以改变的范围的扩大。

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