Entry trajectory planning using quasi-equilibrium glide assumption

An entry trajectory planning problem of high lift-to-drag ratio vehicle which satisfies multi-constraints, such as heat rating, dynamic pressure, over load, boundary conditions and so forth, is studied. Firstly, based on simplified conditions, reduced equations of motion and equilibrium glide conditions, entry trajectory planning of multi-constraints is converted into a parameter searching problem. In order to satisfy down range and lateral error accuracy of spacecraft, an iterate method is used to obtain the values of two parameters which correspond to the magnitude and the sign of the control variable. In simulation analysis, a typical trajectory planning problem of multi-constraints is considered, and results indicate that the method can efficiently generate a feasible entry trajectory which satisfies all practical constraints.