(A) convex programming-based approach to trajectory optimization for survivability enhancement of homing missiles

Abstract

the adjoint method is applied to efficiently compute the miss distance objective. Using the adjoint method based on the system impulse response, the miss distance can be analytically derived from the missile homing loop. Then, a sequential convex program (SCP) methodology that computes the optimized trajectory by solving a sequence of convex subproblems is adopted to obtain the optimized trajectory. The proper convexification process for the nonlinear, nonconvex optimal control problem, which is included the equivalent transformation technique for the objective function, the relaxation for the constraints, and the partial linearization for the system dynamics, is performed. Numerical examples on a homing scenario of an air-to-surface missile toward a stationary target demonstrate the validity and efficacy of the proposed convex program-based method compared to traditional nonlinear program approaches. This paper attempts on-board trajectory planning and optimization using sequential convex programming which needs the convexification process for the nonlinear, nonconvex optimal control problem. The trajectory optimization results using the sequential convex programming method are faster than the optimization results of the nonlinear programming method. The significance of this thesis is to show that the convex optimization approach can be applied to complex and practical nonlinear optimal control problems such as three-dimensional trajectory optimization problems and to provide additional solutions to quickly solve these problems.

This paper addresses the trajectory optimization of the attacking homing missiles to simultaneously consider the homing performance and evasive maneuver against the defending interceptors. Planning the optimal trajectory for evasive maneuver of the homing missiles against anti-air defending interceptors in advance is very important for improving the survivability of the homing missiles. The miss distance (interception error) of the interceptor can be obtained by an evasive maneuver of the homing missile during the flight time for which the interceptor intercepts the homing missile. An optimal control problem that maximizes the miss distance from the interceptor while ensuring zero homing error is presented