This paper addresses the problem of midcourse guidance of dual-pulse rocket motor interceptors with seeker field-of-view constraints using singular perturbation technique. The guidance law considers a combination of terminal velocity and flight time as a performance measure. In addition to the seeker field-of-view limit, constraints in the optimization problem include minimum dynamic pressure limit arising due to aerodynamic controllability. Using the time scale separation between the state variables, the full-order problem is reduced into lower-order subproblems, and a closed-form solution for guidance law is derived. It is shown that the performance of the interceptor is not very sensitive to perturbation of pulse firing time, and an offline generated lookup table is used to time the second thrust pulse firing. The proposed guidance law is computationally efficient, and its performance is benchmarked with that of pseudospectral-based feedback guidance with much lower computational cost. Simulation studies with point mass and six-degree-of-freedom model are presented highlighting the accuracy and efficacy of the proposed guidance law.
Singular-Perturbation-Based Guidance of Pulse Motor Interceptors with Look Angle Constraints
Journal of Guidance, Control, and Dynamics ; 44 , 7 ; 1356-1370
2021-07-01
Article (Journal)
Electronic Resource
English
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