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公开(公告)号：EP1678034A1
公开(公告)日：2006-07-12
申请号：EP04791097.1
申请日：2004-10-31
摘要： This invention relates to a system for launching a payload. A rotating flywheel (11) accelerates a traditionally designed rocket (16) to a significant speed. Rotational energy from the flywheel (11) is transferred in the form of kinetic energy through a spiral surface and a cable (14) to the rocket (16). The system comprises a smaller rocket (16) carrying less fuel, provided with a smaller first stage engine. All other components of the system are re-used. This leads to a simpler and more efficient design of the rocket (16) and to a considerable reduction in launch costs.
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32.发明公开Combined diffuser and recirculation manifold in a propellant or oxidizer tank 有权联合Diffussor和在燃料或Oxydationsmitteltank循环歧管
公开(公告)号：EP1033301A3
公开(公告)日：2001-07-18
申请号：EP00200755.7
申请日：2000-03-03
申请人： The Boeing Company
发明人： Lak, Tibor I. , Rogers, Gene , Weber, James F. , Merlin, Michael V. , Gaynor, Timothy L. III , Davis, John E. , Gerhardt, David L.
CPC分类号： B64G1/402 , F17C5/02 , F17C2221/011 , F17C2221/012 , F17C2223/0161 , F17C2223/033 , F17C2227/0107 , F17C2270/0194 , F17C2270/0197 , Y02E60/321
摘要： A propellant or oxidizer tank system and process for densifying liquid propellant (104) or liquid oxidizer comprises a propellant tank (100) with a combined manifold (102), a combined manifold line (108), a pressurizing gas line (112), and a vent line (114). The combined manifold (102) is located in the tank (100). The combined manifold line (108) functionally connects the combined manifold (102) to a chilling system (18). The pressurizing gas line (112) and the vent line (114) are also functionally connected to the combined manifold line (108). The tank (100) may be disposed in a vehicle. The manifold (102) is disposed proximate the top of the tank (100). The chilling system (18) is a heat exchanger/filling system. The process for filling the tank (100) comprises the steps of charging the tank (100), venting gases (106) in the tank (100), densifying the liquid (104), and pressurizing the tank (100). The tank (100) is charged with the liquid (104) such that the orifices (120) in the combined manifold (102) are submerged. The gases (106) in the tank (100) are vented through the combined manifold (102) and out of the tank (100). The venting step is arrested prior to the submerging of the combined manifold orifices (120). The liquid (104) in the tank (100) is densified by directing a recirculation stream of the liquid propellant (104) or oxidizer from the tank (100) through the combined manifold (102), out of the tank (100), cooling and directing the recirculation stream into the tank (100). The tank (100) is pressurized by directing a pressurizing gas stream into the combined manifold (102) and into the tank (100) after the densifying step.
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33.发明公开SPACE LAUNCH VEHICLES CONFIGURED AS GLIDERS AND TOWED TO LAUNCH ALTITUDE BY CONVENTIONAL AIRCRAFT 失效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
发明人： KELLY MICHAEL S
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.
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公开(公告)号：EP0425664A1
公开(公告)日：1991-05-08
申请号：EP90911407.0
申请日：1990-04-30
申请人： CRISWELL, David R.
发明人： CRISWELL, David R.
摘要： Le système de lancement à usage multiple comprend plusieurs modules différents pouvant être fixés ensemble de manière libérable suivant une pluralité de configurations possibles de lancement. Les modules comprennent une unité de premier étage non habité et au moins partiellement non réutilisable (10) capable d'effectuer des opérations mono-étage-sur-orbite avec ses propres charges internes ou externes, ou en tant que partie d'un système multi-étage-sur-orbite pour des lancements de capacités de charge plus élevées. L'unité de premier étage peut être fixée de manière démontable à d'autres unités de premier étage (10), des unités non motorisées (18) de transport de cargaison, et/ou des véhicules spaciaux habités (14). L'unité de premier étage (10) peut être entièrement non réutilisable après lancement.
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公开(公告)号：EP0335677A3
公开(公告)日：1990-12-27
申请号：EP89303085
申请日：1989-03-29
发明人： FRIED, ISRAEL
CPC分类号： B64G1/002
摘要： A space launcher and method for launching satellites and other payloads into space, comprising multi-stage rockets with payload wherein the ratio of the weight of any lower stage rocket (12) to the weight of the rocket stage (11) directly above it is less than two and a half, and wherein the weight of each rocket stage can be defined as that weight of the space launcher, at the start of firing of this stage, minus the weight of the rocket and payload of the stage directly above it at the time when the latter stage rocket begins firing.
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公开(公告)号：EP0201374A1
公开(公告)日：1986-12-17
申请号：EP86400689.5
申请日：1986-03-28
摘要： Ce système permet de commander un organe (168) dans un ensemble à fonctionnement autonome de courte durée, en particulier une fusée, avec un moyen embarqué (100) lié à cet ensemble, et apte à introduire dans l'organe le fluide hydraulique sous pression par un conduit (141). Ce système comporte en combinaison et embarqués dans l'ensemble à fonctionnement autonome : un réservoir (130) du fluide hydraulique employé lors du fonctionnement autonome, un moyen de mise en pression de ce fluide (110), un conduit (171) évacuant hors de l'ensemble autonome le fluide après qu'il a actionné l'organe.
Application aux fusées.摘要翻译： 该系统能够控制具有短持续时间自主操作的组件中的构件（168），尤其是火箭，其具有连接到该组件的车载装置（100），并且能够在压力下将液压流体引入车身。 通过导管（141）。 该系统包括组合并且以自主操作嵌入在组件中的组件：在自主操作期间使用的液压流体的储存器（130），用于对该流体（110）加压的装置，从该组件中排出的导管（171） 在它启动器官之后自动设置流体。 应用于火箭。
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公开(公告)号：EP4402397A1
公开(公告)日：2024-07-24
申请号：EP21789952.5
申请日：2021-09-15
发明人： KINSMAN, Peter
IPC分类号： F16L37/244 , F16L37/30 , B64G1/40 , B64G5/00 , F02K9/00
CPC分类号： F16L37/30 , F16L37/244 , B64G1/402
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公开(公告)号：EP3831723B1
公开(公告)日：2023-09-27
申请号：EP19843080.3
申请日：2019-09-27
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