Abstract
The trajectory optimization of aerodynamically controlled missiles in the terminal phase is studied using Radau Pseudospectral Method (RPM). We first establish this complex trajectory optimization problem with angle of attack and bank angle as control variables. Impact angle and dynamic pressure constraints are taken into account. Then, the formulation of nonlinear programming problem (NLP) using RPM is stated in detail. Finally, application to hypersonic gliding vehicle is carried out based on GPOPS toolbox and the results illustrate the effectiveness and high accuracy of RPM.
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