Please use this identifier to cite or link to this item: http://hdl.handle.net/11455/9259
標題: 建模、估測及攔截變軌戰術性彈道目標
Modeling, Estimation and Interception of Tactical Ballistic Target with Variable Trajectory
作者: 謝昇霖
Hsieh, Sheng-Lin
關鍵字: 變軌;variable trajectory;誤失距離;曲線導引法;擴增狀態觀測器;miss distance;spline guidance;extended state observer
出版社: 電機工程學系所
引用: [1] X. R. Li, and V. P. Jilkov, “A Survey of Maneuvering Target Tracking—Part II: Ballistic Target Models,” Proceedings of SPIE Conference on Signal and Data Processing of Small Targets, San Diego, USA, July-August 2001. [2] C. L. Lin, Y. P. Lin, and K. M. Chen, “On the design of fuzzified trajectory shaping guidance law,” ISA Transactions, Vol. 48, No. 2, pp. 148-155, 2009 [3] C.F. Lin, “Modern Navigation. Guidance and Control Processing,” Prentice Hall, N. J., 1991. [4] C.F. Lin, “Advanced Control System Design,” Prentice Hall, Englewood Cliffs, N. J., 1994. [5] P. Zarchan, “Tactical and Strategic Missile Guidance,” 5th Ed., AIAA, Washington, D.C., 2007. [6] R.E. Kalman, “A New Approach to Linear Filtering and Prediction Problems,” ASME Journal of Basic Engineering, Series 82d, pp.35-45, 1960. [7] H.W. Sorenson, “Parameter Estimation: Principles and Problem,” Mariel Dekker Inc., N. Y., 1985. [8] T. Yuan, and C. Jian, and R. Zhang, “Design of Three-dimensional Guidance Law Based on Extended State Observer for Hit-to-Kill Interceptors,” Proceedings of the IEEE International Conference on Automation and Logistics, Shenyang, pp. 73-78, 2009. [9] Y. Yao, and Y.H. Wang, “Acceleration estimation of maneuvering targets based on extended state observer,” Control and Simulation Center, Harbin Inst. of Technology, Harbin, 2009. [10] Y.H. Wang, “Design of Lateral Thrust and Aerodynamics Blended Control System Based on Auto Disturbance Rejection Controller,” Control and Simulation Center, Harbin Inst. of Technology, Harbin, 2009. [11] J.L. Song, Z.X. Gan, and J.Q. Han, “Study of Active Disturbance Rejection Controller on Filtering,” Control and Design, Vol. 18, No. 1, 2003. [12] F. Lin, H. Sun, Q. L. Zheng, and Y. F. Xia, “Novel Extended State Observer for Uncertain System with Measurement Noise,” Control Theory and Applications, Vol. 22, No. 1, 2005. [13] Y.H. Wang, Y. Yao, and K.M. Ma, “A New Type Extended State Observer for System with Measurement Noise,” Proceedings of the IEEE International Conference on Automation and Logistics, Qingdao, pp. 1745-1749, 2008. [14] Y.H. Wang, Y. Yao, and K.M. Ma, “Analysis and Application of Fal Function Filter,” Electric Machines and Control, Vol. 14, No. 11, 2010. [15] B.R. Bowring, “Transformation from spatial to geographical coordinates,” Survey Review, volume 23., pp.323-327, 1976. [16] P. Zarchan, “Tactical and Strategic Missile Guidance,” AIAA, Washington, D. C., 1980. [17] R. William, and Jr. Mentzer ”Test and Evaluation of Land-Mobile Missile Systems,” Johns Hopkins APL Technical Digest, Vol. 19, No. 4, pp. 421-435, 1998 [18] G. W. Cherry, “A General Explicit, Optimizing Guidance Law for Rocket- Propellant Spacecraft,” AIAA Paper 64-638, Aug. 1964. [19] Y. H. Li, “Design and Analysis of Medium and Higher-Tier Missile Guidance Law,” Department of Electrical Engineering, National Chung Hsing University, Taichung, TAIWAN, ROC
摘要: 
本論文之目的在於攔截變軌彈道飛彈,因此除了一般傳統飛彈飛行軌跡外,並建立彈道飛彈目標變軌之導引律,提出一估測器,使攔截器得以估測目標逃逸加速度,進而提出攔截器之終端導引律,使其包含目標之逃逸加速度,而達到攔截逃逸目標的性能。
在彈道目標方面,本研究先以曲線導引法建立彈道飛彈變軌後之軌跡,該法除了可依據彈道目標變軌之需求調整第一中間點與第二中間點之位置外,而該軌跡亦能同时滿足誤失距離和終端落角要求;在反彈道飛彈方面則是以擴增狀態觀測器為基礎,針對終端尋標器開啟後,根據所得到之資訊,如相對距離,視線角度及視線角變化率,於彈置計算機上以一個簡單、有效且快速之方法,估測目標之逃逸加速度,最後進行彈道飛彈攔截的導引律設計。

The objective of this research is to intercept tactical ballistic missiles with variable trajectories. We first construct a guidance law to generate variable trajectories for the tactical ballistic target. For the interceptor, an extended state observer (ESO) is designed for estimating the target evasive acceleration. Finally, a terminal guidance is proposed for the interceptor to against the evasive ballistic target by utilizing the target evasive information provided by the ESO.
For the ballistic target, the spline guidance is proposed to construct variable trajectories by setting two middle points. A variety of variable flight trajectories of the target maneuver is investigated and evaluated. As for the interceptor, the target trajectory estimation algorithm is developed based on a 2nd –order ESO using the information acquired from the seeker on the interceptor. Finally, the ESO is incorporated with the guidance law to fulfill the anti-evasive ballistic target’s guidance law design.
URI: http://hdl.handle.net/11455/9259
其他識別: U0005-2208201315061400
Appears in Collections:電機工程學系所

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