Experimental Investigation Of A Gas Dynamic Thrust Vector Control For Hypersonic Space Planes

The feasibility and performance of a gas dynamic thrust vector control for advanced space planes using wall bleeding were investigated experimentally in the form of a parameter variation. In these studies, attempts were made to minimize the required control mass flows taken from the forebody boundary layer or intake. Furthermore, a semiempirical method for the design of the bleeding channel and geometry is presented, as well as a possible application of the results to flight mechanics.