The design of guidance and control laws for missiles traveling at hypersonic speeds is an inherently challenging task due to the fact that the system dynamics are nonlinear and highly coupled. An even more challenging task is the design of guidance laws for hypersonic missiles, which incorporates the terminal conditions to maximize target penetration. In this research, nonlinear control techniques are combined with optimal control methods to develop guidance and control laws for air-breathing hypersonic missiles in the presence of system uncertainty and external disturbances. One of the contributions of this research is detailed theoretical analysis of the performance characteristics of the proposed control design. Moreover, by including terminal constraints in the cost function, target penetration is maximized. Specifically, by minimizing angle of attack (AoA) and inertial angle of obliquity (AoO) at impact, maximum target penetration is achieved. Lyapunov-based stability analysis is utilized to prove the theoretical result, and high-fidelity numerical simulation results are provided to verify the practical performance of the proposed guidance law design.
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