Abstract
In this paper, a set of optimal guidance laws to achieve zero a miss distance as well as a desired impact angle is presented. Each of optimal impact angle control guidance laws is the solution of a linear quadratic optimal control problem in consideration of proper time-varying weighting function into the cost function. This approach is the same way of obtaining “optimal” PNG law with various navigation constants. Proposed optimal impact angle control guidance laws are closely related to the navigation constant of PNG. A simple and practical time-to-go calculation method in consideration of the curved missile trajectory caused by the impact angle control is proposed. Basic properties including error characteristics of proposed laws are also investigated.
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