In this paper, a new impact time and impact angle control guidance law for homing missiles against a stationary target is proposed. To derive a state feedback command for the proposed law with terminal constraints on the impact time and angle, we introduce a polynomial function of the guidance command with three unknown coefficients, one of which is determined to achieve the impact time requirement. The others are determined to satisfy the terminal impact angle constraint, as well as the zero miss distance. Because the proposed guidance law has arbitrary guidance gains, it is possible to shape the intercept trajectory and acceleration command profile by choosing proper gains in relation to the missile's capability, operational conditions, and so on.
Augmented Polynomial Guidance With Impact Time and Angle Constraints
IEEE Transactions on Aerospace and Electronic Systems ; 49 , 4 ; 2806-2817
2013-10-01
2373194 byte
Article (Journal)
Electronic Resource
English
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