Abstract
In the past years many in-depth studies on new launch vehicles with airbreathing engines have been conducted worldwide. The extreme performance requirements and the small design margins for such vehicles have in particular renewed the interest in trajectory optimization. The paper reports on recent progress in the state of the art of numerical techniques and their implementation. Questions of robustness, ease of use, efficiency are addressed; user-and software requirements as well as a particular architecture are described. The prototype of an advanced user-interface is presented. The optimal ascent of an advanced launch vehicle is discussed as an example.
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