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公开(公告)号：US20080237399A1
公开(公告)日：2008-10-02
申请号：US11693645
申请日：2007-03-29
CPC分类号： B64G1/1085 , B64G1/242 , B64G1/26 , B64G2001/643
摘要： A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separation between the satellites is established by allowing one or more of the satellites to drift at one or more orbits having apogee altitudes below an operational orbit apogee altitude. A satellite is maintained in an ecliptic normal attitude during its operational life, in an embodiment. The satellite's orbit is efficiently maintained by a combination of axial, radial, and canted thrusters, in an embodiment. Satellite embodiments include a payload subsystem, a bus subsystem, an outer load path support structure, antenna assembly orientation mechanisms, an attitude control subsystem adapted to maintain the satellite in the ecliptic normal attitude, and an orbit maintenance/propulsion subsystem adapted to maintain the satellite's orbit.
摘要翻译： 实施卫星舰队的方法包括在运载火箭中发射一组卫星。 在一个实施例中，卫星在结构上通过卫星外部负载路径连接在一起。 在与运载火箭分离之后，通过允许一个或多个卫星在具有低于操作轨道远地点高度的远地点高度的一个或多个轨道上漂移来建立卫星之间的节点间隔。 在一个实施例中，卫星在其使用寿命期间保持为黄道正常姿态。 在一个实施例中，通过轴向，径向和倾斜推进器的组合有效地维持卫星的轨道。 卫星实施例包括有效载荷子系统，总线子系统，外部负载路径支持结构，天线组件定向机构，适于将卫星维持在黄道正常态度的姿态控制子系统，以及适于维持卫星的卫星的维护/推进子系统 轨道。
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公开(公告)号：US08639181B2
公开(公告)日：2014-01-28
申请号：US11968271
申请日：2008-01-02
申请人： Glenn N. Caplin , James D. Thompson
发明人： Glenn N. Caplin , James D. Thompson
IPC分类号： H04B7/185
CPC分类号： H04B7/18513
摘要： A system for communications between a lunar or planetary surface and the Earth may include a first communications satellite adapted to be positioned in a predetermined orbit relative to a celestial body. A first antenna may be mounted on the first communications satellite. The first antenna may include a predetermined beam shape for communications between the first communications satellite and an asset on the lunar or planetary surface. A second antenna may also be mounted on the first communications satellite. The second antenna may include a selected beam shape for communications between the first communications satellite and the Earth. A communications system may be included for relaying communications between the first and second antennas.
摘要翻译： 用于月球或行星表面与地球之间通信的系统可以包括适于相对于天体定位在预定轨道中的第一通信卫星。 第一天线可以安装在第一通信卫星上。 第一天线可以包括用于第一通信卫星和月球或行星表面上的资产之间的通信的预定波束形状。 第二天线也可以安装在第一通信卫星上。 第二天线可以包括用于第一通信卫星和地球之间的通信的选择的波束形状。 可以包括用于中继第一和第二天线之间的通信的通信系统。
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3.发明授权公开(公告)号：US07861975B2
公开(公告)日：2011-01-04
申请号：US11394742
申请日：2006-03-31
申请人： John W. Behrens , Thomas L. Kessler , Leora Peltz , Jeffrey J. Cronick , Glenn N. Caplin , Frank O. Chandler , Robert V. Frampton , Daniel E. Rivera
发明人： John W. Behrens , Thomas L. Kessler , Leora Peltz , Jeffrey J. Cronick , Glenn N. Caplin , Frank O. Chandler , Robert V. Frampton , Daniel E. Rivera
IPC分类号： B64G1/64
CPC分类号： B64G1/1078 , B64G1/281 , B64G1/402 , B64G1/646 , B64G2001/247
摘要： An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.
摘要翻译： 空间内航天器维修系统（10）包括维修航天器（22）和推进剂模块（24）。 维修航天器包括客户服务系统（136）以及用于独立飞行操作的导航航空电子设备（108）和维修推进剂罐（170）。 推进剂模块将维修模块从上段脱落位置移动，并将其释放在客舱飞船（16）附近，用于维修任务。 它有一个具有多个任务能力的推进剂坦克（172），用于在任务之间重新填充维修航天器的推进剂罐。 维修航天器和推进剂模块中的一个或两个可以具有导航航空电子设备。 维修航天器还具有用于不同客户航天器的通用对接适配器（70），并可将客户航天器从非合作转换为合作。
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4.发明授权Two part spacecraft servicing vehicle system with adaptors, tools, and attachment mechanisms 有权两部分航天器维修车辆系统与适配器，工具和附件机构公开(公告)号：US07823837B2
公开(公告)日：2010-11-02
申请号：US11394743
申请日：2006-03-31
申请人： John W. Behrens , Thomas L. Kessler , Leora Peltz , Jeffrey J. Cronick , Glenn N. Caplin , Frank O. Chandler , Robert V. Frampton , Daniel E. Rivera
发明人： John W. Behrens , Thomas L. Kessler , Leora Peltz , Jeffrey J. Cronick , Glenn N. Caplin , Frank O. Chandler , Robert V. Frampton , Daniel E. Rivera
IPC分类号： B64G1/64
CPC分类号： B64G1/1078 , B64G1/646
摘要： An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.
摘要翻译： 空间内航天器维修系统（10）包括维修航天器（22）和推进剂模块（24）。 维修航天器包括客户服务系统（136）以及用于独立飞行操作的导航航空电子设备（108）和维修推进剂罐（170）。 推进剂模块将维修模块从上段脱落位置移动，并将其释放在客舱飞船（16）附近，用于维修任务。 它有一个具有多个任务能力的推进剂坦克（172），用于在任务之间重新填充维修航天器的推进剂罐。 维修航天器和推进剂模块中的一个或两个可以具有导航航空电子设备。 维修航天器还具有用于不同客户航天器的通用对接适配器（70），并可将客户航天器从非合作转换为合作。
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公开(公告)号：US20090224105A1
公开(公告)日：2009-09-10
申请号：US12470611
申请日：2009-05-22
CPC分类号： B64G1/1085 , B64G1/242 , B64G1/26 , B64G2001/643
摘要： A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separation between the satellites is established by allowing one or more of the satellites to drift at one or more orbits having apogee altitudes below an operational orbit apogee altitude. A satellite is maintained in an ecliptic normal attitude during its operational life, in an embodiment. The satellite's orbit is efficiently maintained by a combination of axial, radial, and canted thrusters, in an embodiment. Satellite embodiments include a payload subsystem, a bus subsystem, an outer load path support structure, antenna assembly orientation mechanisms, an attitude control subsystem adapted to maintain the satellite in the ecliptic normal attitude, and an orbit maintenance/propulsion subsystem adapted to maintain the satellite's orbit.
摘要翻译： 实施卫星舰队的方法包括在运载火箭中发射一组卫星。 在一个实施例中，卫星在结构上通过卫星外部负载路径连接在一起。 在与运载火箭分离之后，通过允许一个或多个卫星在具有低于操作轨道远地点高度的远地点高度的一个或多个轨道上漂移来建立卫星之间的节点间隔。 在一个实施例中，卫星在其使用寿命期间保持为黄道正常姿态。 在一个实施例中，通过轴向，径向和倾斜推进器的组合有效地维持卫星的轨道。 卫星实施例包括有效载荷子系统，总线子系统，外部负载路径支持结构，天线组件定向机构，适于将卫星维持在黄道正常态度的姿态控制子系统，以及适于维持卫星的卫星的维护/推进子系统 轨道。
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公开(公告)号：US08511617B2
公开(公告)日：2013-08-20
申请号：US12470611
申请日：2009-05-22
IPC分类号： B64G1/00
CPC分类号： B64G1/1085 , B64G1/242 , B64G1/26 , B64G2001/643
摘要： A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separation between the satellites is established by allowing one or more of the satellites to drift at one or more orbits having apogee altitudes below an operational orbit apogee altitude. A satellite is maintained in an ecliptic normal attitude during its operational life, in an embodiment. The satellite's orbit is efficiently maintained by a combination of axial, radial, and canted thrusters, in an embodiment. Satellite embodiments include a payload subsystem, a bus subsystem, an outer load path support structure, antenna assembly orientation mechanisms, an attitude control subsystem adapted to maintain the satellite in the ecliptic normal attitude, and an orbit maintenance/propulsion subsystem adapted to maintain the satellite's orbit.
摘要翻译： 实施卫星舰队的方法包括在运载火箭中发射一组卫星。 在一个实施例中，卫星在结构上通过卫星外部负载路径连接在一起。 在与运载火箭分离之后，通过允许一个或多个卫星在具有低于操作轨道远地点高度的远地点高度的一个或多个轨道上漂移来建立卫星之间的节点间隔。 在一个实施例中，卫星在其使用寿命期间保持为黄道正常姿态。 在一个实施例中，通过轴向，径向和倾斜推进器的组合有效地维持卫星的轨道。 卫星实施例包括有效载荷子系统，总线子系统，外部负载路径支持结构，天线组件定向机构，适于将卫星维持在黄道正常态度的姿态控制子系统，以及适于维持卫星的卫星的维护/推进子系统 轨道。
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7.发明申请Two Part Spacecraft Servicing Vehicle System with Adaptors, Tools, and Attachment Mechanisms 有权具有适配器，工具和附件机构的两部分航天器维修车辆系统公开(公告)号：US20110031352A1
公开(公告)日：2011-02-10
申请号：US12888552
申请日：2010-09-23
申请人： John W. Behrens , Thomas L. Kessler , Leora Peltz , Jeffrey J. Cronick , Glenn N. Caplin , Frank O. Chandler , Robert V. Frampton , Daniel E. Rivera
发明人： John W. Behrens , Thomas L. Kessler , Leora Peltz , Jeffrey J. Cronick , Glenn N. Caplin , Frank O. Chandler , Robert V. Frampton , Daniel E. Rivera
IPC分类号： B64G1/64
CPC分类号： B64G1/1078 , B64G1/646
摘要： An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.
摘要翻译： 空间内航天器维修系统（10）包括维修航天器（22）和推进剂模块（24）。 维修航天器包括客户服务系统（136）以及用于独立飞行操作的导航航空电子设备（108）和维修推进剂罐（170）。 推进剂模块将维修模块从上段脱落位置移动，并将其释放在客舱飞船（16）附近，用于维修任务。 它有一个具有多个任务能力的推进剂坦克（172），用于在任务之间重新填充维修航天器的推进剂罐。 维修航天器和推进剂模块中的一个或两个可以具有导航航空电子设备。 维修航天器还具有用于不同客户航天器的通用对接适配器（70），并可将客户航天器从非合作转换为合作。
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公开(公告)号：US5806800A
公开(公告)日：1998-09-15
申请号：US577596
申请日：1995-12-22
申请人： Glenn N. Caplin
发明人： Glenn N. Caplin
摘要： The present invention is a dual function deployable radiator and radiator cover for use on a communication satellite. A deployable radiator is folded or in a "stowed" configuration over a fixed radiator when a satellite is in a launch vehicle. The deployable radiator thereby serves as insulation for the satellite when heat rejection is not necessary. When heat rejection becomes necessary, the deployable radiators are deployed whereby unwanted heat is rejected from the satellite. The deployable radiators, therefore serve a dual purpose, functioning as insulators for part of a mission and radiators for the remainder.
摘要翻译： 本发明是在通信卫星上使用的双功能可展开散热器和散热器罩。 当卫星在运载火箭中时，可部署的散热器在固定的散热器上折叠或以“收起”的方式配置。 因此，当不需要排热时，可展开的散热器作为卫星的绝缘。 当需要排热时，可部署的散热器被部署，从而从卫星拒绝不希望的热量。 因此，可部署的散热器具有双重目的，作为其他部分任务的绝缘子和散热器。
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公开(公告)号：US08915472B2
公开(公告)日：2014-12-23
申请号：US13604050
申请日：2012-09-05
摘要： A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing. The launch system may include a first space vehicle, a second space vehicle releasably attached to the first space vehicle and oriented relative to the first space vehicle such that, when placed within the fairing, a launch load of the first space vehicle is transmitted to and borne by the second space vehicle. In certain embodiments, the first and second space vehicles each may include one of an electrical propulsion unit and a hybrid chemical and electrical propulsion unit. Use of electrical or hybrid chemical and electrical propulsion units enables the second space vehicle to bear all or a significant portion of the launch load of the first space vehicle, thereby eliminating the need for additional support structure.
摘要翻译： 多空间车辆发射系统，其可以适于被布置在运载火箭整流罩的有效载荷区域内。 发射系统可以包括第一空间飞行器，可释放地附接到第一空间飞行器并相对于第一空间飞行器定向的第二空间飞行器，使得当放置在整流罩内时，第一空间飞行器的发射载荷被传送到 由第二艘太空车承载。 在某些实施例中，第一和第二空间飞行器各自可以包括电推进单元和混合化学和电动推进单元中的一个。 电气或混合化学和电力推进装置的使用使得第二空间车辆能够承载第一空间车辆的所有或大部分发射载荷，从而不需要额外的支撑结构。
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公开(公告)号：US20130299641A1
公开(公告)日：2013-11-14
申请号：US13604050
申请日：2012-09-05
摘要： A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing. The launch system may include a first space vehicle, a second space vehicle releasably attached to the first space vehicle and oriented relative to the first space vehicle such that, when placed within the fairing, a launch load of the first space vehicle is transmitted to and borne by the second space vehicle. In certain embodiments, the first and second space vehicles each may include one of an electrical propulsion unit and a hybrid chemical and electrical propulsion unit. Use of electrical or hybrid chemical and electrical propulsion units enables the second space vehicle to bear all or a significant portion of the launch load of the first space vehicle, thereby eliminating the need for additional support structure.
摘要翻译： 多空间车辆发射系统，其可以适于被布置在运载火箭整流罩的有效载荷区域内。 发射系统可以包括第一空间飞行器，可释放地附接到第一空间飞行器并相对于第一空间飞行器定向的第二空间飞行器，使得当放置在整流罩内时，第一空间飞行器的发射载荷被传送到 由第二艘太空车承载。 在某些实施例中，第一和第二空间飞行器各自可以包括电推进单元和混合化学和电动推进单元中的一个。 电气或混合化学和电力推进装置的使用使得第二空间车辆能够承载第一空间车辆的所有或大部分发射载荷，从而不需要额外的支撑结构。
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