[1] GUELMAN M.The closed-form solutions of pure proportional navigation ［J］.IEEE Transactions on Aerospace and Electronic Systems, 1976, 12(7):526-532.

[2] YUAN P J, CHERN J S.Ideal proportional navigation［J］.Journal of Guidance, Control and Dynamics, 1992, 15(4):1161-1165.

[3] TAHK M J, RYOO C K, HANGJU C.Recursive time-to-go estimation for homing guidance missiles［J］.IEEE Tran-sactions on Aerospace and Electronic Systems, 2002, 38(1):13-24.

[4] RYOO C K, HANGJU C, TAHK M J.Time-to-go weighted optimal guidance with impact angle constraints［J］.IEEE Transactions on Control Systems Technology, 2006, 14(3):483-492.

[5] LV Y J, WANG B G, CHEN X G.The study on improved algorithm for residual flight time estimation［J］.Journal of Projectils, Rockets, Missiles and Guidance, 2012, 32(3):23-26.

[6] VINCENT C L.Time-to-go estimate for missile guidance［C］//AIAA Guidance, Navigation, and Control Conference and Exhibit, San Francisco, California, 2011:151-165.

[7] BEHROUZ E, MOHSEN B, JAFAR R.Optimal sliding-mode guidance with terminal velocity constraint for fixed-interval propulsive maneuvers［J］.Acta Astronautica, 2008, 62:556-562.

[8] ASIF F, DAVID N L.Bank-to-turn missile guidance with radar imaging constraints ［J］.Journal of Guidance, Control and Dynamics, 2005, 28(6):1157-1170.

[9] DWIVEDI P N, TIWARI S N, BHATTACHRYA A.A ZEM dynamics based integrated estimation guidance and control of interceptors［C］//AIAA Guidance, Navigation, and Control Conference, Portland, Oregon, 2011:79-102.

[10] DWIVEDI P N, TIWARI S N, BHATTACHRYA A.A ZEM based effective integrated estimation and guidance of interceptors in terminal phase［C］//AIAA Guidance, Navigation, and Control Conference, Portland, Oregon, 2011:124-148.

[11] CHENG G C.Optimal control theory and method for spacecrafts［M］.Changsha:National University of Defense Technology Press, 1997.

[12] ROBERT W M.A new paradigm in optimal missile gui-dance［D］.Tucson: The University of Arizona, 2009.