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完整後設資料紀錄
DC 欄位 | 值 | 語言 |
---|---|---|
dc.contributor.advisor | 傅立成(Li-Chen Fu) | |
dc.contributor.author | Po-Hsu Huang | en |
dc.contributor.author | 黃柏徐 | zh_TW |
dc.date.accessioned | 2021-06-15T02:44:54Z | - |
dc.date.available | 2011-08-20 | |
dc.date.copyright | 2009-08-20 | |
dc.date.issued | 2009 | |
dc.date.submitted | 2009-08-10 | |
dc.identifier.citation | [1] Wikipedia, 'List of missiles,' http://en.wikipedia.org/wiki/List_of_missiles.
[2] H. D. Hoelzer, 'Range Normalized Coordinates for Optimal Angle-Only Tracking in Three Dimensions', Teledyne-Brown Engineering, Huntsville, AL, Nov. 25, 1980. [3] D. V. Stallard, “An Angle-Only Tracking Filter in Modified Spherical Coordinates,” AIAA Journal of Guidance & Control and Dynamic, Vol. 14, No. 3, 1991. [4] R. R. Allen and S. S. Blackman, “Implementation of an Angle-only Tracking Filter,” Signal and Data Processing of Small Targets, Vol.1484, pp. 292-303, 1991. [5] S.S. Blackman and S. H. Roszkowski, “Application of IMM Filtering To Passive Ranging,” Proc. SPIE, Vol.3809, pp. 270-281, 1999. [6] Y. Bar-Shalom and X. Li, “Estimation and Tracking: Principles, Techniques and Software,” Artech House, 1993. [7] M. T. Busch and S. S. Blackman, “Evaluation of IMM filtering for an air defense system application,” Proc. of Signal and Data Processing of Small Targets, Vol. 2561, pp. 435-447, 1995. [8] E. Mazora, A. Averbuch, Y. Bar-Shalom and J. Dayan, “Interacting Multiple Model Methods in Target Tracking: A Survey” IEEE Transactions on Aerospace and Electronic Systems, Vol. 34, No. 1, Jan 1998. [9] D. Mosier and M. K. Sundareshan, “A Multiple Model Algorithm for Passive Ranging and Air-to-Air Missile Guidance,” Signal and Data Processing of Small Targets, pp 222-233, 2001. [10] N. VPS, G. Girija and N. Shanthakumar, “Three Model IMM-EKF for Tracking Targets Executing Evasive Maneuvers,” Aerospace Sciences Meeting and Exhibit, Reno, Nevada, Jan 2007. [11] S. S. Blackman and R. Popoli “Design and Analysis of Modern Tracking Systems,” Artech House, 1999. [12] T. Erlandsson. “Angle-Only Target Tracking,” Linkopings Universitet, Sweden, 2007 [13] S. A. Murtaugh and H. E. Criel, 'Fundamentals of proportional navigation,' IEEE Spectrum, vol. 3, pp. 75-85, 1966. [14] M. Guelman, 'Closed-form solution of true proportional navigation,' IEEE Transactions on Aerospace and Electronic Systems, vol. 12, pp. 472-482, 1976. [15] C. D. Yang and F. B. Yeh, 'Closed-form solution for a class of guidance laws,' Journal of Guidance & Control and Dynamics, vol. 10, pp. 412-415, 1987. [16] C. D. Yang, F. B. Yeh, and J. H. Chen, 'The closed-form solution of generalized proportional navigation,' AIAA Journal of Guidance & Control and Dynamic, vol. 10, pp. 216-218, 1987. [17] U. S. Shukla and P. R. Mahapatra, 'The proportional navigation dilemma - pure or true? ,' IEEE Transactions on Aerospace and Electronic Systems, vol. 26, pp. 382-392, 1990. [18] K. R. Babu, I. G. Sarma and K. N. Swamy, “Switched Bias Proportional Navigation for Homing Guidance Against Highly Maneuvering Target,” AIAA Journal of Guidance, Control, and Dynamics, Vol. 17, No. 6, pp. 1357–1363, 1994. [19] K. R. Babu, I. G. Sarma, and K. N. Swamy, “Two Variable-Structure Homing Guidance Schemes With and Without Target Maneuver Estimation,” AIAA Paper 94-3566, Aug. 1994. [20] S. D. Brierley, and R. Longchamp, “Application of Sliding-Mode Control to Air-Air Interception Problem,” IEEE Transactions on Aerospace and Electronic Systems, Vol. 26, No. 2, pp. 306–325 , 1990. [21] D. Zhou, C. Mu, and W. Xu, “Adaptive Sliding-Mode Guidance of a Homing Missile,” AIAA Journal of Guidance & Control and Dynamic, Vol. 22, No. 4, July-August, pp. 589-593, 1999. [22] B. Wie, H. Weiss, and A. Arapostathis, 'Quaternion feedback regulator for spacecraft eigenaxis rotations,' AIAA Journal of Guidance, Control, and Dynamics, vol. 12, pp. 375-380, 1989. [23] F. K. Yeh, H. H. Chine, and L. C. Fu, 'Nonlinear optimal sliding mode midcourse controller with thrust vector control,' Proceedings of the American Control Conference, vol. 2, pp. 1348-1353, 2002. [24] Y. H. OH, 'Three dimensional interpolation method for missile aerodynamics,' AIAA Aerospace Sciences Meeting, 27th, Reno, NV, 1989. [25] 鄭凱元, 'Rocket controller design with TVC and DCS,' Department of Electrical Engineering, National Taiwan University, Master Thesis, 2002. [26] 葉富光, 'Variable structure theory based integrated guidance/autopilot design for maneuvering flying vehicles,' Department of Electrical Engineering, National Taiwan University, Ph.D. Dissertation, 2003. [27] 鄭家豪, 'Novel guidance law and autopilot designs for intercepting Missiles and launch rockets with TVC and DCS,' Department of Electrical Engineering, National Taiwan University, Master Thesis, 2004. [28] 葉俊文, 'Adaptive controller design for launch rockets with TVC and DCS,' Department of Electrical Engineering, National Taiwan University, Master Thesis, 2005. [29] 林以凡, 'Novel control design for intercepting missiles with highly maneuverable autopilot system,' Department of Electrical Engineering, National Taiwan University, Master Thesis, 2006. [30] 薛民雄, 'Novel controller design for missiles to intercepting maneuvering target,' Department of Electrical Engineering, National Taiwan University, Master Thesis, 2007. [31] S. Gutman, 'Applied min-max approah to missile guidance and control ' American Institute of Aeronautics and Astronaustic, 2005. [32] Missile Defense Agency, U. S. Department of Defense, http://www.mda.mil [33] P. Zarchan, 'Tactical and Strategic Missile Guidance,' American Institute of Aeronautics and Astronautics, Inc, vol. 99, 2002. [34] J. R. Wertz, 'Spacecraft Attitude Determination and Control,' Kluwer Academic Publishers, 1978. | |
dc.identifier.uri | http://tdr.lib.ntu.edu.tw/jspui/handle/123456789/44206 | - |
dc.description.abstract | 在恐怖主義高漲以及資源競爭激烈的時代,為了防範及保衛國土的安全,國防工業的發展勢必為國家安全最重要的指標。其中,飛彈系統的研究是各國競相發展的重點武器之一。本篇論文討論飛彈系統的三個主要決策部分:偵搜器,導引法則以及自動駕駛儀。首先,在偵搜器的設計中,我們使用被動式測距技術來實現,其原理係利用交互式多模型(Interacting Multiple Models)結合修正球座標(Modified Spherical Coordinate)下之延伸卡爾曼濾波器(Extended Kalman Filter)來偵察以及追蹤目標物的軌跡以及相對資訊;導引率的部分,考量目標估測中產生的誤差,利用順滑模態控制理論(Sliding Mode Control)來進行設計。此外,針對自動駕駛儀,我們同樣利用順滑模態控制理論來實現。在整合飛彈系統的過程中,我們考量姿態誤差造成的影響來修正導引率,其穩定性則藉由李奧普洛夫定理(Lyapunov Stability Theory)來分析及證明。在飛彈模型方面,我們使用了無翼面的彈體設計。使用無翼面彈體的好處是可以讓空氣動力學的非線性效應對飛彈的影響減到最小。在動力方面則使用推力向量控制(Thrust Vector Control)及側噴流控制系統(Divert Control System),這可以讓飛彈的活動範圍自大氣層內延伸至外太空。為了驗證所設計控制器的性能,我們做了多樣的模擬,並且將空氣動力模型包含在其中。透過不同場景的模擬,來驗證本篇論文提出的被動式測距以及整合飛彈系統。最後,比較不同的目標物機動運動,來分析與討論系統的可行型與穩定性。 | zh_TW |
dc.description.abstract | This thesis presents the three main parts of the missile system: estimator/seeker, guidance Law and autopilot system. The estimator/seeker is developed with a passive ranging law by using angle-only measurements for acquiring better covert operation. The guidance law is designed with the sliding-mode theory, for minimizing the distance between the missile and the target. The autopilot system based on quaternion representation is also designed using sliding mode control method to generate the attitude command. The stability of the integrated guidance/autopilot system is proved with Lyapunov stability theory. In addition, the actuator of missile is equipped with Thrust Vector Control (TVC) and Divert Control System (DCS) in order to extend the operation range from endo-atmosphere to exo-atmosphere. Finally, various simulations incorporating aerodynamics model are presented to verify the validity of the proposal Seeker/Estimator and integrated Guidance/Autopilot systems, and we compare the performance of the simulations with that from the previous works. Moreover, the simulation results reveal that the mission of intercepting a maneuvering target is successful. | en |
dc.description.provenance | Made available in DSpace on 2021-06-15T02:44:54Z (GMT). No. of bitstreams: 1 ntu-98-R96921009-1.pdf: 1027726 bytes, checksum: 61ff59f946e49bac083795cd318486a9 (MD5) Previous issue date: 2009 | en |
dc.description.tableofcontents | 中文摘要................................................i
Abstract...............................................ii Table of Contents.....................................iii List of Figures.........................................v List of Tables........................................vii Chapter 1 Introduction..................................1 1.1 Motivation of Research..............................1 1.2 Introduction of Types of Missiles...................1 1.3 Survey of Related Works.............................5 1.4 Contribution........................................8 1.5 Organization........................................9 Chapter 2 Preliminaries and Problem Description........11 2.1 Fundamentals of Estimator/Seeker..................11 2.2 Missile Guidance Law...............................12 2.2.1 Proportional Navigation..........................12 2.3 Airframe and Actuators.............................16 2.3.1 Thrust Vector Control and Divert Control System..16 2.3.2 Airframe Modeling................................17 2.4 Aerodynamics.......................................22 2.5 Mathematical Background............................27 2.5.1 Dynamics in Changing Coordinate..................27 2.5.2 Attitude Representation..........................29 2.5 Problem Description................................34 Chapter 3 Seeker/Estimator Design......................37 3.1 Missile Control System............................37 3.2 Passive Ranging Law................................38 3.2.1 Modified Spherical Coordinates...................40 3.2.2 Extended Kalman Filter...........................41 3.2.3 Initial Covariance Matrix........................44 3.2.4 Process Noise and Measurement Noise Matrix.......45 3.3 Multiple Models Filter............................46 3.3.1 State and Covariance Mixing......................47 3.3.2 IMM Sub-filter...................................49 Chapter 4 Missile Guidance Law Design..................55 4.1 Modeling for interception..........................55 4.2 Sliding Mode Guidance Law......................... 61 Chapter 5 Integrated Guidance/Autopilot System Stability Analysis...............................................68 5.1 Autopilot System...................................68 5.2 Integrated Guidance/Autopilot System...............75 Chapter 6 Simulations and Analysis.....................83 6.1 Missile Integrated G/A System......................83 6.2 Non-maneuvering Target.............................87 6.3 Maneuvering Target.................................92 Chapter 7 Conclusion..................................102 Reference.............................................104 | |
dc.language.iso | en | |
dc.title | 針對具被動式測距技術之攔截飛彈控制器設計 | zh_TW |
dc.title | Novel Control Design for Intercepting Missile with Passive Ranging System | en |
dc.type | Thesis | |
dc.date.schoolyear | 97-2 | |
dc.description.degree | 碩士 | |
dc.contributor.oralexamcommittee | 張帆人(Fan-ren Chang),馮蟻剛(I-Kong Fong),王立昇,練光祐 | |
dc.subject.keyword | 被動式測距,順滑模態,推力向量控制,側噴流控制系統,李奧普洛夫定理, | zh_TW |
dc.subject.keyword | Passive ranging,Sliding mode control,Thrust Vector Control,Diver Control System,Lyapunov stability theory,Maneuvering target, | en |
dc.relation.page | 107 | |
dc.rights.note | 有償授權 | |
dc.date.accepted | 2009-08-10 | |
dc.contributor.author-college | 電機資訊學院 | zh_TW |
dc.contributor.author-dept | 電機工程學研究所 | zh_TW |
顯示於系所單位: | 電機工程學系 |
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