Abstract
Terminal velocity maximization of air-to-air agile missiles during agile turn phase is studied. It is important to make sure that agile missiles have enough velocity after agile turn stage in order to impact the target. The agile turn is operated during the boost phase. Thus, the agile turn problem is formulated as terminal velocity maximization with given final time. Optimal solutions are obtained by two different methods, pseudospectral method and parameterized costate optimization method. The parameterized costate optimization method is a part of shooting method of indirect method which is proposed to verify the solutions obtained by pseudospectral method. At first, the basic missile model with constant axial acceleration is treated in the two dimensional yaw plane. After looking into the basic missile model, missile model with aerodynamic forces and thrust is analyzed.
Highlights
In the last few decades, advances in aircraft maneuvering technology continued to produce new challenges for antiair weapon systems
This paper investigates the optimal control problem by proposing ‘parameterized costate optimization method’
2.1 Simple missile model without control bound A simple missile model is employed in two dimensional yaw plane optimal control problem in order to verify pseudospectral method with parameterized costate optimization method
Summary
In the last few decades, advances in aircraft maneuvering technology continued to produce new challenges for antiair weapon systems. The agile turn problems are focused on the first two stages which are the key issues of missiles’ performance because these stages affect the missiles’ launch envelope These stages are accomplished during the boost phase. Solving an optimal control problem by setting cost function as minimum agile turn time may make velocity decrease significantly. It is undesirable since it cannot use relative velocity that is earned from the launch aircraft and may results into mission failure. It is one of the shooting methods of indirect method which transforms the problem from the original optimal control problem to finding initial values of costates By using this method to a simple missile model, solutions obtained by applying pseudospectral method [6] can be verified. Numerical optimization is conducted on missile model with aerodynamic forces and thrust
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