非爆破型分離機構之設計與驗證;The Design and Verification of Separation Mechanism using Non-explosive Actuator

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題名:	非爆破型分離機構之設計與驗證;The Design and Verification of Separation Mechanism using Non-explosive Actuator
作者:	錡紳民;Chi,Shen-min
貢獻者:	機械工程研究所
關鍵詞:	非爆破型致動器;分離機構;熱熔線;驗證測試;Non-explosive actuator;Validation tests.;Hot-melting wire;Separation mechanism
日期:	2012-08-08
上傳時間:	2012-09-11 18:19:22 (UTC+8)
出版者:	國立中央大學
摘要:	本論文旨在發展出一新型非爆破型分離機構(Non-explosive actuator separation mechanism，以下簡稱NEA分離機構)，並透過各式實驗以驗證相關之設計功能。本研究不只可增進航太研究之自主設計與開發能力，並可提供國內自主衛星、探空火箭等酬載分離任務之所需。本研究先進行國內外NEA分離機構相關文獻之收尋，並對其進行分析。將分析結果利用型態設計圖表之概念，並利用 “死點原理”與 “自助原理”等設計原理，完成一新型扁平設計之非爆破型分離機構之概念設計，其中包括 (a)非爆破型致動器和(b)解鎖機構等兩模組設計。非爆破型致動器中採用熱熔線做為觸發裝置，致動時通以一高電流作為啟動訊號。分離機構利用一分裂螺帽達成螺栓結合之任務需求，可承受50 kg 之靜態、10G之動態衝擊等負載，以及在6G隨機振動、無啟動訊號下不會產生鬆脫解鎖。本研究除完成細部設計，並加工、組裝出機構原型，以進行功能驗證測試。為確保NEA分離機構可滿足設定之任務各種要求，本研究亦進行以下功能驗證測試，項目包括 (i)靜態負載測試、(ii)動態衝擊測試、(iii)隨機振動測試以及(iv)分離解鎖之振動值量測。在靜態負載測試中，利用自行設計之封閉式加載測試治具，以油壓方式設定不同測試負載，隨後進行分離測試，以驗證在各種不同負載情況下之分離功能。在動態衝擊測試與隨機振動中以「垂直動電式振動試驗機」輔以測試治具，以探空酬載驗收之規格進行測試。最後並以加速規量測NEA分離機構在分離解鎖時所造成之振動值。完成所有驗證測試後，本研究之設計具備通過50 kg靜態負載測試、動態衝擊測試與動態隨機振動之負載承受能力。負載測試後進行分離功能驗證，其解鎖所需時間為靜態負載0.4秒與動態隨機振動0.2秒。此差異推測是動態負載造成之微設定(Micro-setting)效應。經由微設定驗證結果指出動態負載確實縮短整體解鎖時間。最後以加速規量測解鎖造成之衝擊值，最大加速度發生在與螺栓脫離之軸心相反方向，其值約為7.4g。The main purpose of the thesis is to developed a new type of separation mechanisms with a non-explosive actuator (NEA mechanism), and to validate its functions through various tests. The results of the research can not only improve the independent design and develop abilities of domestic aerospace research, but also can fulfill the requirements for separation of the satellite mission or the sounding rockets missions in Taiwan.In this study, the related literature and patents about NEA mechanism are searched and analyzed systematically. A morphological chart was thus established, from that the concept design was derived together with “principle of toggle point ” and “principle of self-help”. The new type of NEA mechanism with a flat design involves two modules, namely (a) the non-explosive actuator and (b) the separation mechanism. The Non-explosive actuator used the hot-melting wire as triggering device, which is triggered by high current. The separation mechanism is designed with a split nut for connection with a bolt. It is designed as to support a static load of 50 kg as well as an impact load of 10G. It is also able to remain the connection under random vibration of 6G while no trigger signal is available. A prototype of the NEA mechanism based on the detail design is built for the validation tests.The function validation tests are initiated to ensure the proposed NEA mechanism having the capability of fulfillment of various requirements of the missions. The conducted tests are (i) static load test, (ii) impact load test, (iii) random vibration test and (iv) measurement of the separation impact. In the static load test, the separation performance of the NEA mechanism is conducted on a force closure fixture with a manually operated hydraulic pump for load generation. Both the impact load test and random vibration test were conducted on a “vertical move-in vibration test machine”, following to the environment testing process for sounding rocket payload’s acceptance.After all tests validate that NEA mechanism can not only pass through the static load test and impact load test, but also the vibration load test. The separation time by the static load test and by the dynamic load test is about 0.4 seconds and 0.2 seconds, respectively. A possible reason for this time difference is the dynamic micro-setting effect. By conducting an experiment for micro-setting, it is very clear that dynamic vibration load do shorten the separation time. At last, we measure the impact with the accelerometer, which caused by the separation. The max acceleration is detected at the opposite of the bolt detachment axis direction, which is approximate 7.4G.
顯示於類別:	[機械工程研究所] 博碩士論文

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