Integrated truss type small satellite main force bearing structure and design optimization method

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Integrated truss type small satellite main force bearing structure and design optimization method

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LUO QING / LI DONGXU / FAN CAIZHI / WANG JIE / ZHOU GUOHUA / ZHOU LILIN / TU YONGGANG / HAN MINGFEN

The invention belongs to the technical field of spacecraft structure design, and discloses an integrated truss type small satellite main force bearing structure and a design optimization method, the integrated truss type small satellite main force bearing structure comprises a middle plate, a truss type supporting structure and a bottom plate, wherein the middle plate and the bottom plate are arranged in parallel to serve as an installation bearing structure of a satellite load, the middle plate and the bottom plate are connected through a truss type supporting structure, and a butt joint mechanism used for being connected with a carrier rocket in a butt joint mode is arranged on the side, away from the truss type supporting structure, of the bottom plate. Compared with a traditional smallsatellite main force bearing structure, the overall supporting rigidity of the satellite structure is improved, the structural stability is improved, the mass of a structural system is reduced, the internal space size of a small satellite is increased, and the internal space use efficiency of the satellite is improved. In addition, a good installation supporting point can be provided so as to adapt to the requirements of satellite assembly and complex wiring of the whole satellite cable for the installation point.

本发明属于航天器结构设计技术领域，本发明公开了一种一体化桁架式小卫星主承力结构及设计优化方法，一体化桁架式小卫星主承力结构包括中板、桁架式支撑结构和底板，所述中板和底板两者相互平行布置作为卫星负载的安装承载结构，所述中板和底板之间通过桁架式支撑结构相连，所述底板远离桁架式支撑结构的一侧设有用于连接与运载火箭对接的对接机构。本发明相比与传统的小卫星主承力结构，不仅提高了卫星结构的整体支承刚度，提升了结构稳定性，减小了结构系统的质量，增大了小卫星内部的空间体积，提升了卫星内部的空间使用效率。此外，本发明还能够提供良好的安装支撑点，以适应卫星总装、以及整星电缆复杂走线对安装点的需求。

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Title :

Integrated truss type small satellite main force bearing structure and design optimization method

Additional title:

一体化桁架式小卫星主承力结构及设计优化方法

Contributors:

LUO QING (author) / LI DONGXU (author) / FAN CAIZHI (author) / WANG JIE (author) / ZHOU GUOHUA (author) / ZHOU LILIN (author) / TU YONGGANG (author) / HAN MINGFEN (author)

Publication date :

2021-03-26

Type of media :

Patent

Type of material :

Electronic Resource

Language :

Chinese

Classification :

IPC:

B64G Raumfahrt , COSMONAUTICS / F16M Rahmen, Gehäuse oder Grundplatten von Kraftmaschinen oder anderen Maschinen oder von Apparaten, nicht auf eine besondere Art von Maschine oder Apparat eingeschränkt, die anderweitig vorgesehen ist , FRAMES, CASINGS, OR BEDS, OF ENGINES OR OTHER MACHINES OR APPARATUS, NOT SPECIFIC TO AN ENGINE, MACHINE, OR APPARATUS PROVIDED FOR ELSEWHERE / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung