To solve the missile guidance with constraints of impact time and terminal impact angle, a time and angle control guidance law based on optimal error dynamics is designed, and a definite performance index is given. The expression of time to go estimation under generalized optimal angle control guidance law is derived. To reach zero tracking error in the finite time with the optimal convergence pattern, the designed guidance law adds the feedback of impact time error to the generalized guidance law of optimal angle control and considers the impact time error as the tracking error, achieving the joint control of the impact time and the terminal impact angle. The effectiveness of the proposed guidance law is validated through numerical simulations under different conditions.
LI Bin
,
LIN Defu
,
HE Shaoming
,
BAI Bing
. Time and angle control guidance law based on optimal error dynamics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018
, 39(11)
: 322215
-322225
.
DOI: 10.7527/S1000-6893.2018.22215
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