Elastic issues and vibration reduction in a tethered deorbiting mission

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• 作者：Marco Sabatini^a ; ^{marco.sabatini@uniroma1.it" class="auth_mail" title="E-mail the corresponding author} ; Paolo Gasbarri^b ; Giovanni B. Palmerini^a
• 关键词：Space tethers ; Dynamic modeling ; Deorbiting thrust ; Vibration reduction ; Slack tether ; Modeling inaccuracies
• 刊名：Advances in Space Research
• 出版年：2016
• 出版时间：1 May 2016
• 年：2016
• 卷：57
• 期：9
• 页码：1951-1964
• 全文大小：3659 K

文摘

Recently proposed mission concepts involving harpoons or nets to capture and de-orbit debris represent an interesting application of the tethered systems, where the orbiting bodies are connected by a flexible link. These systems present a complex behavior, as flexible characteristics combine with orbital dynamics. The focus of the paper is on the dynamic behavior of the tethered system in the final phase of the de-orbiting mission, when a powerful apogee motor is used to change the debris orbit. The thrust action introduces significant issues, as elastic waves propagate along the tether, and the relevant oscillations couple with the orbital dynamics. Input shaping techniques are proposed to limit or cancel these oscillations. However, the performance of these techniques drops when non-ideal scenarios are considered. In particular, an initially slack tether is a serious issue that must be solved if acceptably low oscillations of the tether are to be obtained. Three strategies are proposed and discussed in this paper to remove the slack condition: a natural drift of the chaser by means of a single impulse, a controlled maneuver for precisely adjusting the relative distance between chaser spacecraft and debris, and a retrieval mechanism for changing the tether length.