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公开(公告)号：US10589879B2
公开(公告)日：2020-03-17
申请号：US15616803
申请日：2017-06-07
发明人： Jeff Aaron Baldwin , Jonathan Noland , Alfred Heikal Tadros , Jeffrey Donald Stoen , Adam Maher
摘要： A first spacecraft and a second spacecraft are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. In the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement. The spacecraft are configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft. A first onboard propulsion subsystem of the first spacecraft includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit. A propellant line arrangement detachably couples the first onboard propulsion subsystem with a second propellant storage arrangement on the second spacecraft.
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公开(公告)号：US20180093786A1
公开(公告)日：2018-04-05
申请号：US15689993
申请日：2017-08-29
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
CPC分类号： B64G1/10 , B64G1/002 , B64G1/1078 , B64G1/222 , B64G1/64 , B64G1/646 , B64G4/00 , B64G2001/1092 , B64G2004/005
摘要： A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
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公开(公告)号：US20200247563A1
公开(公告)日：2020-08-06
申请号：US16855356
申请日：2020-04-22
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
摘要： A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
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公开(公告)号：US10661918B2
公开(公告)日：2020-05-26
申请号：US15689993
申请日：2017-08-29
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
摘要： A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
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公开(公告)号：US20180354659A1
公开(公告)日：2018-12-13
申请号：US15616803
申请日：2017-06-07
发明人： Jeff Aaron Baldwin , Jonathan Noland , Alfred Heikal Tadros , Jeffrey Donald Stoen , Adam Maher
CPC分类号： B64G1/402 , B64G1/002 , B64G1/007 , B64G1/242 , B64G1/26 , B64G1/401 , B64G1/405 , B64G1/64 , B64G1/641 , B64G1/645 , B64G2001/643
摘要： A first spacecraft and a second spacecraft are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. In the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement. The spacecraft are configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft. A first onboard propulsion subsystem of the first spacecraft includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit. A propellant line arrangement detachably couples the first onboard propulsion subsystem with a second propellant storage arrangement on the second spacecraft.
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公开(公告)号：US20160304219A1
公开(公告)日：2016-10-20
申请号：US15098122
申请日：2016-04-13
摘要： A first satellite and a second satellite are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. The launch vehicle includes a primary payload adapter and the first satellite includes a secondary payload adapter. In the launch configuration, the first satellite is mechanically coupled with the primary payload adapter and the second satellite is mechanically coupled with the secondary payload adapter. Following injection into a first orbit by the launch vehicle, the first satellite separates from the primary payload adapter while the second satellite is mechanically coupled with the secondary payload adapter. The second satellite is detached from the secondary payload adapter of the first satellite only after an orbit transfer maneuver executed by a propulsions system of the first satellite. In the launch configuration, the mass of the second satellite is at least 30% of the mass of the first satellite.
摘要翻译： 第一卫星和第二卫星被配置成在发射配置中一起放置在一起，以由单个运载火箭发射。 运载火箭包括主要有效载荷适配器，并且第一卫星包括辅助有效载荷适配器。 在发射配置中，第一颗卫星与主要有效载荷适配器机械耦合，第二颗卫星与辅助有效载荷适配器机械耦合。 在由运载火箭注射到第一轨道之后，第一卫星与主有效载荷适配器分离，而第二卫星与辅助有效载荷适配器机械耦合。 只有在由第一颗卫星的推进系统执行的轨道转移操作之后，第二颗卫星才从第一颗卫星的辅助有效载荷适配器分离。 在发射配置中，第二颗卫星的质量至少为第一颗卫星质量的30％。
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