Modelica Stage Separation Dynamics Modeling for End-to-End Launch Vehicle Trajectory Simulations

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

Ladda ner artikelhttp://dx.doi.org/10.3384/ecp14096589

Ingår i: Proceedings of the 10th International Modelica Conference; March 10-12; 2014; Lund; Sweden

Linköping Electronic Conference Proceedings 96:62, s. 589-598

Visa mer +

Publicerad: 2014-03-10

ISBN: 978-91-7519-380-9

ISSN: 1650-3686 (tryckt), 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.


Aerospace; launcher staging separation


[1] Decker, J. P. Experimental Aerodynamics and Analysis of the Stage Separation of Reusable Launch Vehicles. NASASP-148, January 1967.

[2] Decker, J. P., and Gera, J. An Exploratory Study of Parallel-Stage Separation of Reusable Launch Vehicles. NASA TN D-4765, October 1968.

[3] Baumgarte, J. Stabilization of Constraints and Integrals of Motion in Dynamical Systems. Computer Methods in Applied Mechanics and Engineering, Vol. 1, No. 1, 1972, pp. 1-16.

[4] Decker, J.P., and Wilhite, A. W. Technology and Methodology of Separating Two Similar Size Aerospace Vehicles Within the Atmosphere.AIAA Paper 1975-29, Jan. 1975.

[5] Bauer, G.L., Cornick, D.E., and Stevenson, R. Capabilities and Applications of the Program to Optimize Simulated Trajectories (POST). NASA CR-2770, 1977.

[6] Ascher, U.M., Chin, H., Petzold, L.R., and Reich, S. Stabilization of constrained mechanical systems with DAEs and invariant manifolds. Journal ofMechanics of tructures and Machines, Vol. 23, 1994, pp 135-157.

[7] Elmqvist, H., Mattson, S.E., and Otter, M. Modelica - An International Effort to Design an Object-Oriented Modeling Language. Summer Computer Simulation Conference, pp. 333-339, 1998, ISBN 1-56555-149-4.

[8] Mattson, S.E., Elmqvist, H., and Otter, M. Physical system modeling with Modelica. Control Engineering Practice, v. 6, pp. 501-510, 1998.

[9] Otter, M., Elmqvist, H., and Mattsson, S.E. The New Modelica Multibody Library. Proceedings of the 3rd International Modelica Conference, Linköping, 2003, p 311-330.

[10] Tartabini, P. V., Bose, D. M., McMinn, J. D., Martin, J. G., and Strovers, B. K. Hyper-X Stage Separation Trajectory Validation Studies. AIAA Paper 2003-5819, August 2003.

[11] Murphy, K.J., Buning, P.G., Pamadi, B.N., Scallion, W.I., and Jones, K.M. Status of Stage Separation Tool Development for Next Generation Launch Vehicle Technologies. AIAA Paper 2004-2595.

[12] Pamadi, B.N., Neirynck, T. A., Covell, P.F., Hotchko, N.J., and Bose, D.M. Simulation and Analyses of StagingManeuvers of Next Generation Reusable Launch Vehicles. AIAA Paper 2004-5185.

[13] Pamadi, B.N., Hotchko, N.J., Jamshid Samareh, Covell, P.F., and Tartabini, P.V. Simulation and Analyses of Multi- Body Separation in Launch Vehicle Staging Environment. AIAA Paper 2006-8033.

[14] Pamadi, B.N., Neirynck, T. A., Hotchko, N.J., Scallion W.I., Murphy, K.J., and Covell, P.F. Simulation and Analyses of Stage Separation of Two-Stage Reusable Launch Vehicles. Journal of Spacecraft and Rockets, Vol. 44, No. 1, January-February 2007, pp 66-80.

[15] Källdahl M. Separation Analysis with OpenModelica. Student thesis, Linköping University, Department of Electrical Engineering, Institutionen f¨r systemteknik, Sweden, 2007.

[16] Toniolo, M., Tartabini, P.V., and Pamadi, B.N. Constraint Force Equation Methodology for Modeling Multi-Body Stage Separation Dynamics. 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008, 10.2514/6.2008-219.

[17] Tartabini, P.V., Roithmayr, C.M., Toniolo,M.D., Karlgaard, C.D., and Pamadi, B. N. Modeling Multibody Stage Separation Dynamics Using Constraint Force Equation Methodology. Journal of Spacecraft and Rockets, Vol. 48, No. 4, July-August 2011, pp 573-583.

[18] Pamadi, B.N., Tartabini, P.V., Toniolo, M.D., Roithmayr, C.M., Karlgaard, C.D., and Samareh, J.A. Application of Constraint Force EquationMethodology for Launch Vehicle Stage Separation. Journal of Spacecraft and Rockets, Vol. 50, No. 1, January-February 2013, pp 191-205.

Citeringar i Crossref