控制衛星進入最終軌道設定之姿態，為一相當複雜的運作程序。在載具升空的過程中，載具上的半固定或非固定負載將形成許多力量去牽制飛行，若能降低載具的負擔將可提昇可靠度以及降低成本。而降低載具環境衝擊的一個方法，是於太空船與載具間提供一個隔離系統。

振動隔離系統已經成功發展於大型太空船上，但小型衛星上仍未實現。本論文的主要目的為評估使用被動阻尼系統作為隔離機制的可行性。而首次應用此隔離系統的衛星為PACE微衛星，PACE是由國立成功大學研發之台灣第一顆自主微衛星。振動數據與振動測試機台將由國家太空中心提供，並用於證實模擬之模型。

此模擬中將評估於與PACE同級的微衛星上，使用振動隔離系統之效能，考量壓力與變形之實驗結果，將顯示此被動阻尼概念之效能。

The deployment of a satellite into its final orbit configuration is a highly-complex operation. During the ascent of the launch vehicle, the spacecraft is subjected to many different quasi-static and dynamic loads. A reduction in launch loads can increase the reliability of a space mission as well as decrease its cost. A way to reduce the environment effect during the launch is to provide an isolation system for the whole spacecraft by inserting the appropriate isolation system between the spacecraft and the launch vehicle.

Vibration isolation systems have been recently developed for large spacecrafts, however it has never been done for small satellites. The primary purpose of this thesis is to assess the concept of a passive damping system to isolate a nanosatellite from the vibration due to the launch environment. The PACE nanosatellite has been used as a start. PACE is the first indigenous nanosatellite developed at the National Cheng Kung University (NCKU) in Taiwan.

The data concerning the vibration testing performed in the facilities of the National Space Organization of Taiwan (NSPO) were available and useful to validate the simulations models. The simulations assess the performances of a vibration isolation system for a nanosatellite similar to PACE. The results concerning the stress and the deformation will particularly show the efficiency of a passive damping concept to isolate the spacecraft from the vibration due to the launch environment.

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