Abstract
An indirect time finite element method is applied to solve the trajectory optimization problem for a multi-stage launch vehicle, and the numerical results are compared with the numerical solutions obtained by using a direct collocation and nonlinear program-ming method. A nonlinear programming problem is solved by the sequential quadratic programming algorithm with an augmented Lagrangian merit function, and the converged Lagrange multiplier is used for estimating the costate variables of the optimal trajectory. As a numerical example, a multi-stage launch vehicle trajectory optimization problem with a control variable constraint is solved, and the results are compared.
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