HARL N,BALAKRISHNAN S N.Impact time and angle guidance with sliding mode control[J].IEEE Transactions on Control Systems Technology,2012,20(6):1 436-1 449.
[7]
LUM K Y,XU J X,KHALID A,et al.Sliding mode guidance law for delayed LOS rate measurement[C]//Proceedings of the AIAA Guidance,Navigation and Control Conference and Exhibit.Honolulu:AIAA,2008:1-11.
[8]
TAL S,MOSH I,ODED M G.Sliding-mode control for integrated missile autopilot guidance[J].Journal of Guidance,Control,and Dynamics,2006,29(2):250-260.
[9]
王妍.可重复使用飞行器末段制导律设计方法研究[D].哈尔滨:哈尔滨工业大学,2010.
[10]
CHANG Chao,LIN De-fu,QI Zai-kang,et al.Study on the optimal terminal guidance law with interception an impact angle[J].Journal of Beijing Institute of Technology,2009,29(3):233-239.(in Chinese)
[11]
ASHWINI R,DEBASISH G.SDRE based guidance law for impact angle constrained trajectories[J].Journal of Guidance,Control,and Dynamics,2009,32(1):320-326.
[12]
ASHWINI R,DEBASISH G.Satisfying terminal angular constraint using proportional navigation,AIAA-2009-6088[R].2009.
[13]
STALLARD D V.Biased optimal guidance for bank-to-turn missile[C]//Proceedings of the American Control Conference.San Francisco:IEEE,1983:1 068-1 077.
[14]
STALLARD D V.An approach to optimal guidance for a bank-to-turn missile[C]//Proceedings of the AIAA Guidance and Control Conference.New York:AIAA,1980:192-202.
[15]
AGGARWAL R K,MOORE C R.Terminal guidance algorithm for ramjet-powered missiles[J].Journal of Guidance,Control,and Dynamics,1992,21(6):862-866.
[16]
WANG Yan.Design method of terminal guidance law for reusable launch vehicle[D].Harbin:Harbin Institute of Technology,2010.(in Chinese)