小型電離層探測儀(Compact Ionosphere Probe, CIP)是先進電離層探測儀(Advanced Ionospheric Probe, AIP)的微型改良版本，後者為福爾摩沙衛星五號(FORMOSAT-5)的科學酬載。從2017年9月在軌開機，運作至今已超過4年，遠高於原先設計的兩年壽命。而CIP建立於AIP的設計，大幅縮小儀器尺寸至0.7U、433克，功耗3.5W，使其能夠放置於立方衛星上使用。CIP能夠現地量測衛星軌道高度的電漿參數，包含離子成分、離子溫度、離子密度及離子速度。本論文將研製新版的CIP，目的是可兼容大多數商用立方衛星的結構並解決原先固有的散熱問題。採用模組化設計，增加RS-485通訊介面。重新設計CIP的印刷電路板，以緊密裝入鋁合金外殼中，使向衛星結構散熱的效果更佳。印刷電路板改採PC104接頭相連接並與衛星本體結構體相容，讓檢修與固裝更容易，也可降低拆裝造成的損壞風險。第一個改良的CIP將用於珍珠號立方衛星任務(Propagation Experiment using Kurtz-Above-band Radio in Low earth orbit, PEARL)，預計2023年5月便可獲得飛試結果。本文同時針對低軌道的電離層環境分析離子濃度量測極限，以建立更詳細的量測軌道高度範圍。 ;Compact Ionosphere Probe (CIP) is a miniature version of Advanced Ionospheric Probe (AIP), the science payload of FORMOSAT-5. It has been in operation for more than 4 years since it started in orbit in September 2017, which is much longer than the two-year lifespan of the original design. The CIP is based on the design of AIP, which significantly reduces the size of the instrument to 0.7U, 433 grams, and consumes 3.5W. CIP is capable of in-situ measuring ion concentrations, velocity, or temperature. This paper will develop a next-generation CIP, which is designed to be compatible with most commercial CubeSat structures and to solve the heat dissipation problems. Not only adopts a modular design and adds an RS-485 communication interface but also redesigned the printed circuit board of the CIP to closely fit the aluminum alloy shell to better dissipate heat to the satellite structure. The printed circuit boards can be connected by PC104 connectors and are compatible with the satellite body structure, which makes maintenance and fixing easier and reduces the risk of damage caused by disassembly and assembly. The next generation CIP will be first used on the Pearl CubeSat mission (Propagation Experiment using Kurtz-Above-band Radio in Low earth orbit, PEARL), with flight test results expected in May 2023. This paper also analyzes the ion concentration measurement limits for the ionospheric environment in low orbits to establish a more detailed measurement orbital height range.
