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系統識別號 U0026-2007201512263000
論文名稱(中文) 旋轉薄膜展開之動態分析與實驗
論文名稱(英文) Dynamic Analysis and Experiment of a Spinning Thin Membrane During Deployment
校院名稱 成功大學
系所名稱(中) 工程科學系
系所名稱(英) Department of Engineering Science
學年度 103
學期 2
出版年 104
研究生(中文) 蕭天皓
研究生(英文) Tien-Hao Hsiao
學號 N96024036
學位類別 碩士
語文別 英文
論文頁數 58頁
口試委員 指導教授-莊哲男
口試委員-莊智清
口試委員-苗君易
中文關鍵字 太陽風帆  旋轉薄膜  氣浮平台  微衛星 
英文關鍵字 solar sail  spinning membrane  air bearing table  CubeSat 
學科別分類
中文摘要 本篇論文中,以離散化的模型來探討並模擬美國國家太空總署 (NASA) 所提出的 heliogyro 太陽風帆飛行器之風帆展開旋轉薄膜之過程,並且以實驗驗證模型之可行性及模擬之正確性。先前已有許多針對此種太陽風帆動態方程式的模擬及研究,但對於旋轉薄膜之展開過程的研究卻相當少。本論文分為兩個部分,首先針對太陽風帆不同的展開方式建立離散化之平面模型,分別對不同模型做動態分析及數值模擬,根據模擬運算之結果,選擇較適於太陽風帆之旋轉薄膜展開的模型。第二部分為太陽風帆之實驗,第一個實驗為氣浮桌實驗,實驗利用氣浮平台以減低摩擦力的影響,進而達到使實驗環境與理論假設更為接近,本實驗主要在於驗證旋轉薄膜展開時在平面上之運動情形,並且以模擬之結果建立實驗模型。第二個實驗為微衛星高空汽球實驗,本實驗利用微衛星作為薄膜之載體,並且藉由氣球升至約30公里高之高度,進行薄膜展開之實驗,此實驗同時也是heliogyro此種太陽風帆旋轉薄膜之低軌實驗。微衛星高空汽球之實驗會有兩次,第一次主要是針對微衛星之系統及通訊抖功能做測試,第二次則是會進行薄膜展開之實驗。此兩種實驗的過程及初步結果會在本論文中呈現,並且藉由實驗結果探討及驗證模擬分析之結果。
英文摘要 In this thesis, discrete models of heliogyro which is proposed by NASA are establish. The equations of motion are derived and the behaviour of spinning thin membrane during deployment is analyzed based on these discrete models. Many studies on dynamic analysis of a spinning membrane have already been existed. However, the studies on deployment of a spinning membrane are rare. There are two main parts in this thesis. First, models are built according to the difference ways of deploying a membrane. The equations of motion are derived and simulations are conducted for both models. The better model for deploying a membrane is chosen according to the simulation results. Two experiment are shown in the second part of this thesis. First experiment is air bearing table experiment. In order to make the experiment environment closer to the assumption, air table is used to decrease the effect of friction. the main purpose of this test is to demonstrate the in-plane motion of spinning membrane deployment. Second test is CubeSat high-altitude balloon experiment. CubeSat is used to mount the membrane and launched to around 30 km by the balloon. The membrane is deployed at this high-altitude. This experiment is also the sub-orbital test. There are two times of this test. For the first test, CubeSat is launched to validate the system and the communication. The membrane is deployed in the second test. The detailed process and preliminary results of both experiments are presented to compare with the analysis and simulation results.
論文目次 1 Introduction . . . . . . . . . . . . . . . . . . . . . . . 1
1.1 Research Background and Motivation . . . .. . . . . . . . 1
1.2 Research Objective and Approach . . . . . . . . . . . . . 2
1.3 Thesis Contribution . . . . . . . . . . . . . . . . . . . 3
1.4 Thesis Organization . . . . . . . . . . . . . . . . . . . 3
2 Development of Solar Sails . . . . . . . . . . . . . . . . 4
2.1 History of Solar Sails . . . . . . . . . . . . . . . . . 4
2.2 Challenges and Current Development. . . . . . . . . . . . 6
3 Motion of Membrane Deployment . . . . . . . . . . . . . . . 8
3.1 Model Description . . . . . . . . . . . . . . . . . . . . 8
3.1.1 Free Unrolling Model . . . . .. . . . . . . . . . . . . 8
3.1.2 Constrained Feed Deployment Model .. . . . . . . . . . 11
3.2 Simulations of the Deployment Models . . . . . . . . . . 14
3.2.1 Simulations of the Free Unrolling Model. . . . . . . . 14
3.2.2 Simulations of the Constrained Feed Deployment Model . 15
3.3 Results . . . . .. . . . . . . . . . . . . . . . . . . . 17
4 Air Table Experiment . . . . . . . . . . . . . . . . . . . 18
4.1 Introduction to the Air Bearing Table. . . . . . . . . . 18
4.2 Design of the Air Table Experiment . . . . . . . . . . . 20
4.3 Digital Image Processing . . . . . . . . . . . . . . . . 21
4.4 Results . . . . . . . . . . . . . . .. . . . . . . . . . 28
5 CubeSat Balloon Experiment . . . . . . . . . . . . . . . 31
5.1 Details of the Balloon Experiment. . . . . . . . . . . . 31
5.2 Introduction to CubeSat . . . . .. . . . . . . . . . . . 34
5.2.1 Structure . . . . . . . . . . .. . . . . . . . . . . . 34
5.2.2 Electrical Power System (EPS) .. . . . . . . . . . . . 35
5.2.3 Communication system (COM) . . . . . . . . . . . . . . 37
5.2.4 Command and Data Handling System (CDHS). . . . . . . . 39
5.2.5 Terminal Node Controller (TNC) . . . . . . . . . . . . 39
5.3 Preparation for Launch . . . . . . . . . . . . . . . . . 40
5.3.1 In-lab-Test . . . . . . . . . . . . . . . . . . . . . 40
5.3.2 Long Range Test . . . . . . . .. . . . . . . . . . . . 48
5.4 Balloon Test Results . . . . . . . . . . . . . . . . . . 50
6 Conclusions and Future Work. . . . . . . . . . . . . . . . 55
6.1 Conclusions . . . . . . .. . . . . . . . . . . . . . . . 55
6.2 Future Work . . . . . . .. . . . . . . . . . . . . . . . 56
Bibliography . . . . . . . . . . . . . . . . . . . . . . . . 57
參考文獻 [1] Richard. H. MacNeal, "The Heliogyro: An Interplanetary Flying Machine," tech. rep., Astro Research Corporation, March 1967.
[2] Richard. H. MacNeal, John. M. Hedgepeth, and Hans. U. Schuerch, “Heliogyro Solar Sailer Summary Report,”tech. rep., National Aeronautics and Space Administration,
Washington, D.C., June 1969.
[3] Richard. H. MacNeal, “Structural Dynamics of the Heliogyro,”tech. rep., National Aeronautics and Space Administration, Washington D.C., May 1971.
[4] Jer-Nan Juang, Chung-Han Hung, and William K. Wilkie, “Dynamics of a Slender Spinning Membrane,”in Jer-Nan Juang’s Astrodynamics Symposium, Texas , June 2012.
[5] C. R. McInnes, “Solar Sailing: Technology, Dynamics and Mission Applications,” Springer, 2004.
[6] L. Friedman, “Solar Sailing Development Program (FY 1977) Final Report Vol I,” Report 720-9, Jet Propulsion Laboratory, January 1978.
[7] R. Blomquist,“Design Study of a Solid-State Heliogyro Solar Sail,”M.S. thesis, Massachusetts Institute of Technology, Cambridge, MA, September 1990.
[8] Osamu Mori, Yoji Shiasawa, Yuya Mimasu, Yuichi Tsuda, Takanao Saiki, Takayuki Yamamoto, Katsuhide Yonekura, Hirokazu Hoshino, and Junichiro Kawaguchi, “Overview of IKAROS Mission,”3rd International Conference on Solar Sailing, Glasgow, June 2013.
[9] Artur Scholz, Jer-Nan Juang, Tien-Hao Hsiao, “Design and Analysis of Heliogyro Sail Deployment System”, Europe Conference on Spacecraft Structure, Material and Environment Testing, April 2014.
[10] Chung-Han Hung, “Dynamic Analysis and 3D Simulation of a Spinning Thin Membrane,”MS thesis, National Cheng Kung University, January 2012.
[11] William K. Wilkie, Jerry E. Warren, Jer-Nan Juang, Lucas G. Horta, Karen H. Lyle, Justin D. Littell, Robert G. Bryant, Mark W. Thompson, Phillip E. Walkemeyer, Daniel V. Guerrant, Dale A. Lawrence, S. Chad Gibbs, Earl H. Dowell, Andrew F. Heaton, “Heliogyro Solar Sail Research at NASA,”Advances in Solar Sailing, Springer, 2014.
[12] Jung-Kuo Tu, Shi-Hua Wu, and Chen-Chi Chu, "Platform for Attitude Control Experiment (PACE): An Experimental Three-Axis Stabilized CubeSat," (2004).
[13] Jyh-Ching Juang, Chiu-Teng Tsai, Yung-Fu Tsai, Jiun-jih Miau, "From Hands-on Project Learning to an international Collaborated Satellite Research/Education Project," International Conference on Engineering Education, Gliwice, Poland. 2010.
[14] Artur Scholz, Jer-Nan Juang "Toward open source CubeSat design." Acta Astronautica 115 (2015): 384-392.
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