In this paper results of a trajectory optimization and aerothermodynamic analyses of an Apollo capsule are presented using a time efficient combination of methods. The trajectory optimizations are performed with the optimal control tool FALCON.m to minimize the heat load on a capsule while re-entry. The aerothermodynamic analyses are performed with a coupled Euler/Boundary layer method of second order (KEGSEC) on the determined optimal trajectory. First, trajectory optimizations are performed with different initial flight path angles. The trajectory resulting in the smallest maximum heat flux is chosen to be investigated with respect to the aerothermodynamic loads. In the aerothermodynamic investigations the stagnation point temperatures, the wall temperature distribution, the pressure coefficients and the skin friction coefficients at the critical points on the trajectory are computed and analyzed.     «

In this paper results of a trajectory optimization and aerothermodynamic analyses of an Apollo capsule are presented using a time efficient combination of methods. The trajectory optimizations are performed with the optimal control tool FALCON.m to minimize the heat load on a capsule while re-entry. The aerothermodynamic analyses are performed with a coupled Euler/Boundary layer method of second order (KEGSEC) on the determined optimal trajectory. First, trajectory optimizations are performed wi...     »