Trajectory Optimization of a Transatmospheric Vehicle

Optimal ascent and descent trajectories of a two-stage vehicle are investigated. Two new trajectory optimization methods are shortly described: One is a direct collocation code, the other one is a code based on parameterizing the control functions together with a multiple shooting approach. Both methods do not use adjoint differential equations. They are attached to an advanced user interface with graphical input and output. Numerical results for the ascent from Europe into a 28.5° inclined circular orbit are given.