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A. Wiegand, F. Cremaschi, S. Winter, S. Weikert, T. Link, D. Zell, J. Albinger
The design process of launch vehicles is a complex process with partly diverging objective functions and constraints which are often not defined by technical reasons. So much more it is important to map the technical aspects in an efficient design process. This paper starts with the design processes of the past 15 years and presents the newest developments in multidisciplinary optimisation (MDO) of launch vehicles and GNC sizing. The most critical aspect of the launch vehicle design is the estimation of the structural mass. In the frame of an ESA technology development Astos Solutions has coupled together with MT Aerospace the ascent trajectory and vehicle optimisation with a structural optimisation on substructure level. This allows the estimation of the structural mass as function of stiffening concept, material, geometry and dimensioning load cases, which are directly depending on the optimised trajectory and attitude control. In addition a preliminary design of propulsion systems is optimised followed by a simple performance analysis which is again coupled with the load cases. The design is finalized with an analysis of the controllability in combination with the aerodynamics. The GNC system sizing allows a more detailed consideration of the controllability and of the GNC performance sizing thrust vector and attitude control systems. The consideration of flexible dynamics creates a link back to the structural optimisation which provides a finite element model for purpose of Eigen frequency analysis. The advantages of the new design process are discussed followed by an outlook and conclusion.
Deutscher Luft- und Raumfahrtkongress 2014, Augsburg
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2015
Conference Paper
21,0 x 29,7 cm, 8 Seiten
Stichworte zum Inhalt:
Leistungsanalyse, Trägersystemoptimierung
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