摘要(英) |
The purpose of this paper is to analyze the structure of the Pearl (Propagation Experiment using Kurz-Above-band Radio in Low earth orbit, PEARL) series cube satellites, It is mainly equipped with the K/Ka-band communication experimental payload (K/Ka-band Communication Payload, KCP) developed by RAPIDTEK TECHNOLOGIES INC. and the CIP (Compact Ionosphere Probe) scientific payload developed by the Space Payload Laboratory of National Central University, and Analyze these two CubeSats, PEARL-1C and PEARL-1H, equipped with the Communication Payload (CPL) of Tron Future Technology and the camera module of Foxconn Technology Group. The PEARL CubeSat is expected to use SpaceX′s Falcon 9 rocket to deploy to a low earth orbit (Low Earth Orbit, LEO) mission 550 kilometers above the Earth’s surface, and its orbit is in the form of a sun synchronous orbit (Sun Synchronous Orbit, SSO). Therefore, this paper will focus on analyzing the various external forces exerted by the launch environment on the PEARL, as well as its orbital thermal simulation on the mission orbit, to assess whether the structural design of the Pearl can pass the test of the launch environment and the space environment. |
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