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11. 发明公开

EP1162139A4 REUSABLE BOOSTER FOR THE FIRST STAGE OF A LAUNCHER 有权
标题翻译：可重复使用的火箭配件为运载火箭的第一阶段
公开(公告)号：EP1162139A4
公开(公告)日：2003-01-02
申请号：EP00970361
申请日：2000-10-13
申请人： FGUP G KOSM N PROIZV TS IM M V
发明人： KISELEV ANATOLY IVANOVICH , MEDVEDEV ALEXANDR ALEXEEVICH , TRUFANOV JURY NIKOLAEVICH , RADUGIN IGOR SERGEEVICH , KUZNETSOV JURY LEONIDOVICH , PANKEVICH ALEXANDR ALEXANDROVI , NABOISCHIKOV GENNADY FEDOROVIC , USHAKOV VLADIMIR MIKHAILOVICH
IPC分类号： B64C3/38 , B64G1/00 , B64G1/14 , B64G1/40 , F02K9/78
CPC分类号： F02K9/78 , B64G1/002 , B64G1/14 , B64G1/401
摘要： The invention relates to space rockets and can be used in the production of all-azimuth rockets to put space vehicles onto reference orbits. The booster includes a body which contains tanks for oxidant and for fuel, a shroud for the nose section, an intertank section and a tail section, a rocket engine, an integrally rotatable wing which is directed in the axis of the accelerator during the launching stage and is directed at 90 DEG during re-entry, a three-point landing system and a docking unit for docking with the second stage of the launcher. The booster is provided with air-breathing engines having air intakes and gas pipes with ejection nozzles protruding outside the outline. The fuel system includes tanks in the wing and consumable and balancing tanks in the nose section. The wing is mounted on the upper surface of the booster body, in the region of the intertank section. The horizontal stabilizer has the form of a surface consisting of two rotatable integral outer wings with a low negative V angle, whereby the vertical stabilizer has the form of a fin with a rudder. The cap is provided with a rotary plug for air intake.

12. 发明公开

EP1163152A2 PAYLOAD CARRY AND LAUNCH SYSTEM 有权
标题翻译：系统换着穿，启动有效载荷
公开(公告)号：EP1163152A2
公开(公告)日：2001-12-19
申请号：EP99972835.5
申请日：1999-12-29
申请人： Space Access, L.L.C. , Scott, Harry , Wurst, Stephen G.
发明人： SCOTT, Harry , WURST, Stephen, G.
IPC分类号： B64G1/14
CPC分类号： B64G1/401 , B64G1/005 , B64G1/007 , B64G1/14 , B64G1/402 , F02K7/10 , F02K7/12 , Y02T50/672
摘要： The reusable space launch system (1) embodiment has a first stage vehicle or aerospacecraft (50), a second stage vehicle or reusable spacecraft (51) and a third stage vehicle or reusable orbit transfercraft (52). All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of control surfaces to supply lift, stability and control. The aerospacecraft (50) is configured to use ejector ramjet engines (18) for powered flight and includes equipment to capture air to supplement oxidizer for the ejector ramjet engine (18) during take-off and extreme high altitude. In order to optimize aerospacecraft (50) performance in a pull up movement to exit the sensible atmosphere, the aerospacecraft (50) may include auxiliary ascent rocket engines (116). The aerospacecraft (50) has a payload bay that is accessed by nose load re-closable payload fairings (74).

13. 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。

14. 发明公开

EP0925223A4 LOW EARTH ORBIT PAYLOAD LAUNCH SYSTEM 失效
标题翻译： ERDNAHEN轨道，STARTSYSTEM
公开(公告)号：EP0925223A4
公开(公告)日：1999-12-15
申请号：EP97942518
申请日：1997-09-15
申请人： WURST STEPHEN G , SCOTT HARRY
发明人： WURST STEPHEN G , SCOTT HARRY
IPC分类号： B64C37/02 , B64D5/00 , B64G1/14 , B64G1/64 , B64G1/40
CPC分类号： B64G1/14 , B64D5/00
摘要： The orbital launch system is a three stage vehicle to launch orbital payloads. The system uses a turbofan powered aircraft (2) as the first stage with an aerospacecraft (3) attached by an under wing pylon (8) at an aircraft engine mount (7) for carriage. The aerospacecraft (3) is the second stage and is powered by ejector ramjet engines (27). The aerospacecraft has a cargo bay (6) with cargo bay doors (35) in its midsection. A booster rocket (5) with the payload (9) is launched from the cargo bay (6) by use of an ejection system. The payload (9) is mounted on the booster to be placed in the proper orbit. The orbital launch system may also have a parachute drop recovery system (13) to recover the booster rocket (5) after it deorbits.
摘要翻译：轨道发射系统是发射轨道有效载荷的三级载体。该系统使用涡轮风扇动力飞机（2）作为第一级，其中航空器（3）通过飞机发动机支架（7）处的下翼式挂架（8）附接以用于运输。航空航天器（3）是第二级，由喷射式冲压喷气发动机（27）提供动力。航空航天器在其中部具有货舱（6）和货舱门（35）。具有有效载荷（9）的助推器火箭（5）通过使用弹出系统从货舱（6）发射。有效载荷（9）安装在助推器上，放置在合适的轨道上。轨道发射系统也可以具有降落伞下降回收系统（13），以便在其解吸后回收增压火箭（5）。

15. 发明公开

EP0793599A4 SPACE LAUNCH VEHICLES CONFIGURED AS GLIDERS AND TOWED TO LAUNCH ALTITUDE BY CONVENTIONAL AIRCRAFT 失效
标题翻译： AS滑翔FINISHED FRAMED支持飞船，通过传统的飞机LAUNCH海拔TOWED
公开(公告)号：EP0793599A4
公开(公告)日：1999-04-14
申请号：EP95939846
申请日：1995-11-13
申请人： KELLY SPACE & TECHNOLOGY INC
发明人： KELLY MICHAEL S
IPC分类号： B64C37/02 , B64C25/08 , B64D3/00 , B64D5/00 , B64G1/00 , B64G1/14 , B64G5/00
CPC分类号： B64G1/005 , B64C25/08 , B64D3/00 , B64G1/007 , B64G1/14 , B64G5/00
摘要： Orbital launch vehicles (1) with aerodynamic lifting surfaces (2) enabling them to be towed as gliders behind conventional aircraft (19), and the method of towing these launch vehicles using a flexible cable (18) to connect them with a conventional aircraft (19), for placing spacercraft (15) into low earth orbit at greatly reduced cost compared to current orbital launch systems. The lift from the aerodynamic surfaces (2) enables the launch vehicles (1) to be towed by means of a flexible cable (18) from a conventional runway using existing aircraft (19). As with "conventional air-lauch", this permits spacercraft launch into orbit to originate from any conventional runway consistent with constraints of public safety, thus eliminating the need to build dedicated launch pads at geographic locations from which a full range of orbital inclinations can be reached.

16. 发明授权

EP0631931B1 SPACECRAFT WITH AN ESCAPE SYSTEM FOR THE CREW 失效
标题翻译： WITH A救援体系TEAMS航天器
公开(公告)号：EP0631931B1
公开(公告)日：1998-02-18
申请号：EP94914254.1
申请日：1993-08-04
申请人： MESTON, Vyacheslav Alexandrovich
发明人： MESTON, Vyacheslav Alexandrovich
IPC分类号： B64G1/14 , B64G1/62 , B64C29/00 , B64C39/00
CPC分类号： B64G1/14 , B64G1/62
摘要： The spacecraft comprises: a fuselage (1), a wing (2), a motor unit comprising two liquid fuel launch rocket motors (3), two liquid fuel booster rocket motors (4), six transverse thrust rockets (5) mounted in the fuselage on a rotatable ring (6), solid fuel rocket motors (7 and 8) to provide emergency braking and additional acceleration respectively, a payload compartment (9), the crew's compartment (10), and a tail assembly with two vertical struts (11), a lower stabilizer (12) and an upper stabilizer (13). The fuselage (1) is provided with a movable central conical element (14). The spacecraft chassis is provided with a rotatable rear wheel (21). The crew's compartment (10) is situated between the two upright struts (11) below the upper stabilizer (13). The spacecraft is provided with an orbital manoeuvering system whose final control elements are low thrust motors (22, 23) and gyrodines. The escape system comprises a separate compartment (24) designed as a ballistic re-entry capsule and secured to the aft end of the fuselage. The capsule (24) is linked to the crew's compartment (10) by means of a passage (25) which is provided with a system for getting the crew from their compartment (10) into the capsule (24). The capsule (24) is provided with hatches at the front and rear ends, an aerodynamic braking system and a parachute system. The front part of the capsule (24) is provided with a heat-resistant protective layer (36). The capsule's centre of gravity is displaced towards its forward end.

17. 发明授权

EP0319212B1 Apparatus and method for docking spacecraft 失效转让
标题翻译：装置和用于停放宇宙飞船方法。
公开(公告)号：EP0319212B1
公开(公告)日：1994-01-12
申请号：EP88311207.0
申请日：1988-11-25
申请人： Space Industries, Inc.
发明人： Johnson, Caldwell C. , Faget, Maxime A.
IPC分类号： B64G1/14
CPC分类号： B64G1/646

18. 发明授权

EP0238840B1 Nutzlasttransport- und -betriebseinrichtung für Raumfahrzeuge 失效
标题翻译：空载车辆负荷运输和操作系统
公开(公告)号：EP0238840B1
公开(公告)日：1991-05-15
申请号：EP87102229.9
申请日：1987-02-17
申请人： ERNO Raumfahrttechnik Gesellschaft mit beschränkter Haftung
发明人： Kerstein, Lothar , Ries, Manfred , Weydandt, Jürgen
IPC分类号： B64G1/10 , B64G1/14
CPC分类号： B64G1/22 , B64G1/14

19. 发明公开

EP0364569A4 ROCKET-POWERED, AIR-DEPLOYED, LIFT-ASSISTED BOOSTER VEHICLE FOR ORBITAL, SUPRAORBITAL AND SUBORBITAL FLIGHT 有权转让
标题翻译：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：EP0364569A4
公开(公告)日：1990-11-28
申请号：EP89904991
申请日：1989-03-08
申请人： ORBITAL SCIENCES CORPORATION II
发明人： ELIAS, ANTONIO, LUIS
IPC分类号： B64D5/00 , B64G1/00 , B64G1/14 , B64F1/04
CPC分类号： B64G1/002 , B64D5/00 , B64G1/005

20. 发明公开

EP0194287A4 SATELITE TRANSFER VEHICLE. 有权转让
标题翻译： SATELLITENTRANSPORTANLAGE。
公开(公告)号：EP0194287A4
公开(公告)日：1989-01-24
申请号：EP85904528
申请日：1985-08-28
申请人： SCOTT SCIENCE & TECH , BALLARD DAVID , LOFTS DENNIS
发明人： BALLARD DAVID , LOFTS DENNIS
IPC分类号： B64G1/10 , B64G1/00 , B64G1/14 , B64G1/40 , B64G1/64
CPC分类号： B64G1/641 , B64G1/002 , B64G1/007 , B64G1/1085 , B64G1/14 , B64G1/401 , B64G1/402 , B64G2001/643
摘要： A transfer vehicle (41) for use in a system for transferring payloads from an earth-launch vehicle in one space trajectory to another space trajectory. The system includes an earth-launch vehicle (43) (Fig. 9) with primary propulsion and guidance systems, a transfer vehicle (41) (Fig. 1) carrying a payload which is stowed in the cargo bay (44) during earth-launch and insertion of the earth-launch vehicle (43) into low-earth transfer trajectory. An engine module (10) (Fig. 3) carries on-board mission equipment, rocket engine (23), related fuel supply (26), guidance equipment, attitude control equipment and electrical power supply equipment (Figs. 11-20). A grapple system (33, 42) on the earth-launch vehicle (43) (Fig. 9) deploys the transfer vehicle (41) and cargo and restows it for on-orbit repair/modification for earth-return. The transfer vehicle (41) may by multi-staged (Fig. 21) and may be provided with multiple engines (71) (Fig. 23).

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