探空火箭回收艙之結構設計與品質管制

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題名:	探空火箭回收艙之結構設計與品質管制
作者:	黃臣暉;Chen-Huei Huang
貢獻者:	機械工程研究所
關鍵詞:	品質管制;結構設計;探空火箭酬載回收艙;and quality control;reentry capsule of sounding rocket;structure design
日期:	2009-07-17
上傳時間:	2009-09-21 12:06:12 (UTC+8)
出版者:	國立中央大學圖書館
摘要:	本論文旨在探討我國探空八號火箭之酬載回收艙結構設計。探空八號回收試驗任務主要延續探六回收艙功能並且再次執行回收計畫。探八回收艙預計增加2.4GHz信號通訊功能，以提高回收機率，同時也將增加單機推進系統酬載，以進行太空中控制姿態等相關測試。因內部酬載重量增加，本次任務增加浮球裝置設計讓回收艙可在海面上漂浮，等待搜救任務。本論文亦探討品質控管，使得設計的缺失製造與測試前能有效管制並且進行改善，以確保設計品質並提高可靠度。本次任務之回收艙是採用模組化的設計，在結構上依不同功能採用分層設計並且必須讓各艙內電控模組與儀器等在任務執行階段皆能相互通訊。針對各模組需求，規劃內部酬載原件與主結構結合設計，包含避震結構設計、窗戶結構設計、浮球機構開啟設計等重要設計，完成回收艙結構。其中在避震結構的設計上, 採八處楔形避振墊之密實設計方式, 除可以節省空間, 並可以有效加強在徑向, 軸向以及旋轉上的減震成效。而浮球開啟機構為首次使用非火工爆炸分離式(NEA)的設計理念以達成浮球外殼與艙體脫離，使浮球開啟填氣時，不會是任何電子模組受到衝擊等干擾。為避免重複探六在設計上的疏失，影響本次任務的成功。本研究中亦分別利用失效樹分析(FTA)與失效模式與效應分析(FMEA)等兩種方法管制整體的設計品質。首先應用失效樹分析法找出當初探六回收艙在設計上對加工管制的不足，而可能會造成降落傘艙防護功能失效之原因，以避免探八回收艙犯相同的設計錯誤。同時也藉由失效模式與效應分析方法，建立設計審查表據以分析設計內容，以減少設計異常之發生，降低後續加工與任務執行失敗的機率。探八回收艙目前已完成回收艙整體設計與雛型加工，設計仍待後續相關環境測試之驗證。而本研究所發展之失效模式與效應分析之設計品質管制方法，確實可改善目前的設計缺失，以提升整體的可靠度。 The main purpose of the thesis is to design a reentry capsule for the Taiwan sounding racket mission 8. The reentry capsule is improved in this project based on the result of then sounding racket mission 6. The 2.4GHz channel communication module is attached to the reentry capsule,for example,which can increase the probability of rescue. In addition, a new payload module, the rocket combustion system, is included in the reentry capsule for attitude control test in the space. Because of the increased weight of the capsule in the project,a balloon device is developed so that the capsule can float on the sea as waiting for rescuing. This thesis also develops the quality control methods for design of reentry capsule. The possible faiures can be controlled and improved before manufacturing and the environment tests. The reliability of the designed capsule can be therefore increased. Based on the concept of modular design, the reentry capsule is divided into different capsule modules according to the specified functions and mission. In order to enable the communication of the electric and electronic control modules in each capsule module, a special design for mechanical and also electrical connection between two adjacent capsule modules was also developed. Considering the requirements of each module,the different functional units such as suspension mechanisms for electronic devices and the shell-opening mechanism for the ballon-capsule were also integrated with the corresponding capsule module. By using wedge-cushions the suspension mechanism enables not only to reduce the vibrstions and impacts in axial, radial and rotational direction, but also to realize a compact design for the capsule. The shield-shell of the balloon capsule is opened by a separation mechanism using a non-explosive actuator. The design can prevent the impacts on the electronic control modules when the shield-shells are opening. The design quality of the developed reentry capsule is also controlled by using “Fault Tree Analysis” and “Failure Mode & Effect Analysis”. The possible design defects of the last mission were at first analyzed by using “failure tree analysis”. The defects are redesigned and corrected to avoid the potential failures. Based on the methods of failure mode & effect analysis, the sheets for design review were also established, which are able to decrease the failure probability during manufacture and fly mission. Up to now the design and prototype of the reentry capsule has been completed. The functions of the design must be validated by the further environment tests. However the quality control methods developed in the thesis was verified that they can improve the design quality and also increase the reliability.
顯示於類別:	[機械工程研究所] 博碩士論文

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