The invention discloses a method for designing a direct insertion type main bearing structure of a high-heat-flux cubesat, which comprises the following steps of: firstly, determining the boundary dimension of the main bearing structure, then determining the wall thickness of the main bearing structure, designing the main bearing structure, designing a shady surface shell and an end cover, and finally designing the main bearing structure. And finally, white paint coatings are sprayed to the outer surfaces of the shady face shell and the end cover, and black anodic oxidation treatment is conducted on the interior of the structure. The satellite-borne component supporting structure and the cubesat shell are integrated to increase the contact area, so that the heat conduction efficiency is improved, the device is suitable for the current cubesat with high heat flux, and the problems that the contact area of the existing cubesat structure and the in-satellite component is limited, so that heat dissipation is difficult, and installation is complex are solved.
本发明公开了一种高热流密度立方星的直插式主承力结构设计方法,包括如下步骤:首先确定主承力结构的外形尺寸,接着确定主承力结构的壁厚,再对主承力结构进行设计,接着进行背阴面壳体设计和端盖设计,最后对背阴面壳体和端盖的外表面喷涂白漆涂层、对结构内部进行黑色阳极氧化处理。本发明通过将星载元件支撑结构与立方星外壳一体化以提高接触面积,进而提高了热传导效率,适用于目前高热流密度的立方星,解决了现有的立方星结构与星内元件接触面积有限而使散热困难以及安装复杂等问题。
Design method of direct insertion type main load-bearing structure of high-heat-flux cubesat
一种高热流密度立方星的直插式主承力结构的设计方法
2022-07-22
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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