無人機(jī)制導(dǎo)控制算法的設(shè)計(jì)開題報(bào)告(參考版)
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【正文】 圖1 導(dǎo)彈制導(dǎo)與控制一體化設(shè)計(jì)結(jié)構(gòu)圖 目標(biāo)、主要特色及工作進(jìn)度 ； ； ； ； ；： 第13周 資料查詢，完成開題報(bào)告 第46周 導(dǎo)彈三通道控制建模第714周 導(dǎo)彈制導(dǎo)建模、導(dǎo)彈制導(dǎo)與控制一體化建模、自適應(yīng)滑模一體 化控制器的設(shè)計(jì) 第1516周 軟件仿真 第1718周 撰寫論文和答辯五、參考文獻(xiàn)[1] D. E. Williams. Design of an Integrated Strap down Guidance and Control System for a Tactical Missile. AIAA832169, 1983. [2] J. Evers, J. Cloutier, C. Lin, et al. Application of Integrated Guidance and Control Schemes to a Precision Guided Missiles//Proceedings of 1992 American Control Conference. Chicago, USA, 1992:3225~3230. [3]C. Lin. Optimal Design of Integrated Missile Guidance and Control[R]. AIAA985519, 1998 [4]N. Palumbo, B. Reardon, R. Blauwkamp. Integrated Guidance and Control for Homing Missiles. Johns Hopkins APL Technical Digest, 2004, 25(2):121~139. [5]S. Vaddi, P. Menon, E. Ohlmeyer. Numerical SDRE Approach for Missile Integrated Guidance Control. Journal of Guidance, Control, and Dynamics, 2009,32(2):699~703. [6]M. Xin, S. N. Balakrishnan, E. J. Ohlmeyer. Integrated Guidance and Control of Missiles with θD Method. IEEE Transactions on Control Systems Technology,2006, 14(6):981~992.[7]P. Das, C. Chawla, R. Padhi. Robust Partial Integrated Guidance and Control of Interceptors in Terminal Phase. AIAA20096275, 2009. [8]宋建梅, 張?zhí)鞓? 滑模變結(jié)構(gòu)在導(dǎo)彈制導(dǎo)與控制中的應(yīng)用綜述. 彈箭與制導(dǎo)學(xué)報(bào),1999, (4):32~38[9J. Choi, D. Chwa. Adaptive Nonlinear Guidance Considering Target Uncertainties and Control Loop Dynamics. IEEE Transactions on Aerospace and elec
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