Bewertung der Manoevrierbarkeit gefluegelter Raumtransporter im Entwurfsprozess

Based on the winged space transportation system Hermes a method for maneuverability assessment of a given design model is presented. It differs from previous methods by a high adaptability to design modifications and parameter variations. Maneuverability assessment is performed by maneuver simulation of the design model and comparison of results with specified criteria. The report elaborates on the preparation of the design model for maneuver simulation, and, based on this model, the layout of an attitude control system for optimal use of aerodynamic and reaction controls to perform the required maneuvers. It is highlighted, how high performance as well as easy adaptation to design modifications is achieved by embedding available information about flying behaviour in the control system. The information is extracted from the given design model and flight physics. Example simulations underline the advantages of the control system design philosophy for maneuverability assessment when confronted with a large flight envelope, limited efficiency of controls, and various design model uncertainties. The applicability of the principles of the presented method to different configurations and the usefulness of this within the frame of a future concurrent engineering design process is finally discussed. (orig.)Available from TIB Hannover: RA 2999(96-04) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEDEGerman