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公开(公告)号：US6068211A
公开(公告)日：2000-05-30
申请号：US736874
申请日：1996-10-25
摘要： The present invention is a method of earth orbit space transportation and return utilizing a reusable flyback satellite. A reusable flyback satellite is positioned to a desired release point which provides the capability of the satellite to achieve a desired orbit. The satellite is deployed from that release point. It is then injected into orbit. On-orbit function and services to a payload of the satellite are provided. The satellite is de-orbited, re-entered and landed with airplane-like functionality and utility.
摘要翻译： 本发明是利用可重复使用的回扫卫星进行地球轨道空间运输和返回的方法。 可重复使用的回扫卫星被定位到期望的释放点，其提供卫星实现期望轨道的能力。 从该释放点部署卫星。 然后将其注入轨道。 提供了对卫星有效载荷的在轨功能和服务。 卫星绕轨道，重新进入并着陆，具有类似飞机的功能和效用。
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公开(公告)号：US5513571A
公开(公告)日：1996-05-07
申请号：US245130
申请日：1994-05-17
摘要： An air-breathing, propulsion-assisted projectile designed to be rocket or gun launched and capable of accelerating to hypersonic velocities includes a body having an encompassing cowl, an air compression section, an engine assembly located adjacent the air compression section, and a nozzle section located adjacent the engine assembly. The engine assembly includes apparatus for fuel storage and delivery to a combustion region. The rear end portion of the cowl is configured to direct the exiting combusted air-and-fuel mixture over the nozzle section of the body.
摘要翻译： 设计为火箭或发射枪并能够加速到超音速的空气呼吸的推进辅助射弹包括具有包围的整流罩的主体，空气压缩部分，位于空气压缩部分附近的发动机组件，以及喷嘴部分 位于发动机总成附近。 发动机组件包括用于燃料储存和输送到燃烧区域的装置。 整流罩的后端部构造成将出口的燃烧的空气和燃料混合物引导到主体的喷嘴部分上。
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3.发明申请MULTI-CONSTELLATION GLOBAL NAVIGATION SATELLITE SYSTEM AUGMENTATION AND ASSISTANCE 审中-公开多功能全球导航卫星系统的辅助和辅助公开(公告)号：US20110181465A1
公开(公告)日：2011-07-28
申请号：US12693883
申请日：2010-01-26
申请人： Rongsheng Li , Kamran Ghassemi , Jeff R. Bennett , Michael A. Rizzo, JR. , Jonathan A. Tekawy , Richard T. Cervisi
发明人： Rongsheng Li , Kamran Ghassemi , Jeff R. Bennett , Michael A. Rizzo, JR. , Jonathan A. Tekawy , Richard T. Cervisi
摘要： A multi-constellation GNSS augmentation and assistance system may include a plurality of reference stations. Each reference station may be adapted to receive navigation data from a plurality of different global navigation satellite systems and to monitor integrity and performance data for each different global navigation satellite system. An operation center may receive the integrity and performance data transmitted from each of the plurality of reference stations. A communication network may transmit a message from the operation center to navcom equipment of a user for augmentation and assistance of the navcom equipment.
摘要翻译： 多星座GNSS增强和辅助系统可以包括多个参考站。 每个参考站可以适于从多个不同的全球导航卫星系统接收导航数据，并监视每个不同的全球导航卫星系统的完整性和性能数据。 操作中心可以接收从多个参考站中的每一个发送的完整性和性能数据。 通信网络可以从用户的运营中心向用户的navcom设备发送消息，以增加和辅助navcom设备。
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公开(公告)号：US5402965A
公开(公告)日：1995-04-04
申请号：US122951
申请日：1993-09-20
申请人： Richard T. Cervisi , David M. Toliver , Harry S. Greenberg , Timothy R. Kilgore , Jack H. Arnold , John C. Blake
发明人： Richard T. Cervisi , David M. Toliver , Harry S. Greenberg , Timothy R. Kilgore , Jack H. Arnold , John C. Blake
摘要： A reusable flyback satellite system comprises a refly apparatus and accelerating and positioning apparatus. The refly apparatus provides acceleration and injection into orbit, on-orbit functions services for supporting a payload, de-orbiting, re-entering and landing on a runway. The accelerating and positioning apparatus is attached to a carrier aircraft, the accelerating and positioning apparatus releaseably supporting the refly apparatus. The carrier aircraft positions the accelerating and positioning apparatus at a desired first position wherein the accelerating and positioning apparatus is detached from the carrier aircraft. Thereafter, the accelerating and positioning apparatus positions the refly apparatus to a second position wherein the refly apparatus is detachable from the accelerating and positioning apparatus. The second position is such that the refly apparatus can achieve a desired orbit.
摘要翻译： 可重复使用的回扫卫星系统包括一个装置和加速定位装置。 该装置提供加速和注入轨道，轨道上的功能服务，用于支撑有效载荷，轨道上的轨道，重新进入和降落在跑道上。 加速定位装置安装在载体飞行器上，该加速定位装置可释放地支撑该装置。 载体飞机将加速定位装置定位在期望的第一位置，其中加速定位装置与载体飞行器分离。 此后，加速定位装置将该装置定位在第二位置，其中该装置可从加速定位装置拆卸。 第二位置是使得该装置可以实现期望的轨道。
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