The ascent performance of winged space transportation systems is considered. The system investigated consists of two stages the first stage of which is equipped with an airbreathing propulsion system. For the second stage, two rocket-powered vehicles are considered of which one is equipped with wings and the other is a fuselage type body. It is shown which are key factors in regard to the ascent performance of the upper stage. This particularly concerns the performance enhancement due to its lifting capability. It is shown that an upper stage without wings also shows an ascent capability for small flight path angles at separation. Furthermore, the separation flight maneuver is considered. It is shown that constraints (dynamic pressure and load factor limits) have a significant effect on the ascent performance achievable in regard to a most favorable separation condition for the upper stage. The effects of thrust increase due to a fuel-air ratio more than stoichiometric are considered. It is shown which improvements can be achieved for the separation flight condition. Two optimization methods were used. One is an indirect technique applying the minimum principle and the method of shooting. The other represents a direct technique where the control vector function is parameterized.
Optimal Trajectories for Saenger-Type Vehicles
1990
12 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Ascent trajectories , Space transportation system , Trajectory optimization , Ascent , Flight characteristics , Flight conditions , Flight paths , Stoichiometry , Air breathing engines , Dynamic loads , Dynamic pressure , Fuel-air ratio , Fuselages , Wings , Foreign technology
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