本論文詳述低軌道微衛星電力次系統之發展與實現。此次系統專為國立成功大學之Cheng-Kung University Technology Experimental (CKUTEX) 衛星設計，此衛星為一尺寸36.5 cm x 26.0 cm x 39.9 cm 的微衛星，主要目的為發展一微衛星等級的實驗平台。
　　近年來逐漸累積期望使用較經濟的方法來進行太空實驗，而微衛星即能達成此目的。由於微衛星的尺寸較小，以太陽能為主要電力來源只能產生較少的能量，因此如何將有限產生的電力進行較好的利用是相當重要的。最大功率追蹤法即為其中一個將更多能量從太陽能板上擷取的方法。普遍來說，由於衛星實驗花費相當大，通常皆採用較為簡單而穩定的技術，但即便太陽能最大功率追蹤法對於微衛星等級仍屬新穎，微衛星除了相較於大型衛星較為經濟以外， 對於風險承擔的能力也相對提高。數個適用於微衛星的太陽能最大功率追蹤法已被實現及比較，而此論文中同時詳述各種電力次系統設計時的考量，並且提出一個適用於CKUTEX 衛星的次系統架構，衛星於各個操作階段所需的功能也同樣被實現。

　　The development and implementation of an LEO microsatellite electrical power system is described in the thesis. This system has been designed for the Cheng-Kung University Technology Experimental (CKUTEX) Satellite which is a 36.5 cm x 26.0 cm x 39.9 cm satellite. The main objective of the CKUTEX project is to develop a domestic platform of microsatellite experiment.
　　There are an increasing number of space experiments by using cheaper, lighter microsatellite. With the smaller size of satellite, appropriate management of power source is important. As a result, increasing the efficiency is needed for microsatellites. Peak power tracking (PPT) technique is one of the solutions to harvest more power from solar panel. Simple and stable techniques are usually preferred in space industry because of the high cost to set up a satellite experiment. Even though PPT is recognized as novel in scope of microsatellite, microsatellite is also good at taking risks to test new technology. Several common PPT techniques suitable for microsatellite are implemented and compared. With all the considerations, one power system design suitable for our mission is proposed. Some experiment results are also presented.

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