Nonlinear guidance laws that consider impact time constraints are proposed. Two-dimensional and three-dimensional impact time control guidance laws are derived using Lyapunov stability theory. Under the consideration of the nonlinear kinematics, it is shown that the missile states converge to the desired equilibrium point by the Lyapunov stability theory. The singularity issue of the proposed guidance laws is also analyzed. Numerical simulations are performed to verify the performance of the proposed guidance laws.
Lyapunov-based impact time control guidance laws against stationary targets
IEEE Transactions on Aerospace and Electronic Systems ; 51 , 2 ; 1111-1122
2015-04-01
1988046 byte
Article (Journal)
Electronic Resource
English
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