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公开(公告)号：US06206327B1
公开(公告)日：2001-03-27
申请号：US09282830
申请日：1999-03-31
IPC分类号： B64G100
CPC分类号： B64G1/10 , B64G1/64 , B64G2001/1092
摘要： A mission configurable modular satellite bus structure composed of several scalable modules, including a propulsion module and one or more stackable space modules, each using standard subsystems or components with common structures and/or interfaces, that can be processed in parallel to minimize nonrecurring and recurring costs. Each stackable space module includes a generally cylindrical central hub having a plurality of radial rib panels extending outwardly therefrom to form a plurality of bays for containing subsystem equipment. The hub includes a hollow center sized to receive the propulsion module as a fully assembled unit. The radial rib panels carry the primary structural load of the spacecraft. Also provided are removable side access panels that form enclosures for the bays. The side access panels include equipment mounts along an inside surface for mounting the subsystem components and radiators along an outside surface to provide thermal cooling for the mounted subsystem equipment. The modular bus structure of the present invention is lightweight, stiff, strong, dimensionally stable and is therefore most suitable for highly agile, remote sensing commercial, civil space and government missions. The high degree of access to the spacecraft interior afforded by the present invention allows the various subsystems to be installed as separate, line tested assemblies.
摘要翻译： 任务可配置的模块化卫星总线结构由几个可扩展模块组成，包括推进模块和一个或多个可堆叠空间模块，每个模块可以使用标准子系统或具有公共结构和/或接口的组件，可以并行处理以最小化非正常和重复的 费用 每个可堆叠空间模块包括大致圆柱形的中心毂，其具有从其向外延伸的多个径向肋板，以形成用于容纳子系统设备的多个托架。 轮毂包括一个中空中心，其尺寸适于接收作为完全组装的单元的推进模块。 径向肋板承载着航天器的主要结构载荷。 还提供了形成用于托架的外壳的可拆卸侧面检修面板。 侧面检修面板包括沿着内表面的设备安装件，用于沿着外表面安装子系统部件和散热器，以为安装的子系统设备提供热冷却。 本发明的模块化总线结构是轻质，坚固，坚固，尺寸稳定的，因此最适用于高灵敏度，遥感商业，民用空间和政府任务。 通过本发明提供的对航天器内部的高度访问允许将各种子系统安装为单独的线路测试组件。
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