Paul B. Acquatella
German Aerospace Center (DLR), Institute of System Dynamics and Control, Wessling, Germany
Matthias J. Reiner
German Aerospace Center (DLR), Institute of System Dynamics and Control, Wessling, Germany
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http://dx.doi.org/10.3384/ecp14096589Published in: Proceedings of the 10th International Modelica Conference; March 10-12; 2014; Lund; Sweden
Linköping Electronic Conference Proceedings 96:62, p. 589-598
Published: 2014-03-10
ISBN: 978-91-7519-380-9
ISSN: 1650-3686 (print), 1650-3740 (online)
Stage separation dynamics modeling is a critical capability of future launchers preparatory studies. The development of stage separation frameworks integrable in end-to-end launch vehicle trajectory simulations have been presented in the relevant literature but none profiting from the object-oriented and equation-based acausal modeling properties of Modelica. The objective of this paper is therefore to present such an approach to this problematic. Based on the Constraint Force Equation (CFE) methodology; two case studies to evaluate the proposed approach are considered. Results demonstrate that the approach corresponds very well with the physics behind separation. In addition; we found easiness of implementation of the method within a single environment such as Dymola; demonstrating the benefits of an integrated approach.
