本論文將探討小型電離層探測儀(Compact Ionospheric Probe, CIP)搭載於國立中央大學太空酬載實驗室研製的珍珠號(Propagation Experiment using Kurz-Above-band Radio in Low earth orbit -1C, PEARL-1C)立方衛星和南洋理工大學研製的ELITE衛星之結構設計與模擬分析。小型電離層探測儀為量測電漿特性之科學酬載，為了可以靈活地搭載在不同衛星上，以及解決前一版本小型電離層探測儀的散熱問題，將酬載進行模組化設計。本文將對模組化設計與因應搭載不同衛星的結構設計進行結構模擬分析、熱傳模擬分析與軌道熱模擬分析，以及對實際製作的工程驗證體進行環境測試與驗證分析，以評估小型電離層探測儀的結構設計是否能夠承受火箭發射過程的劇烈條件與太空環境的嚴苛挑戰。;The purpose of this thesis explores the structural design and simulation analysis of the Compact Ionospheric Probe (CIP), mounted on the PEARL-1C (Propagation Experiment using Kurz-Above-band Radio in Low Earth Orbit-1C) CubeSat developed by the National Central University Space Payload Laboratory and the ELITE satellite developed by Nanyang Technological University. The CIP is a scientific payload designed to measure plasma characteristics. To allow flexible mounting on different satellites and to address thermal issues encountered in the previous version of the CIP, the payload has been redesigned with a modular approach. This thesis includes structural simulation analysis, thermal conduction simulation analysis, and orbital thermal simulation analysis for the modular design and its adaptation to different satellites. Additionally, environmental testing and validation analysis were conducted on the engineering model to evaluate whether the CIP′s structural design can withstand the rigorous conditions of rocket launch and the harsh challenges of the space environment.
