Abstract
The paper presents numerical results of a study concerned with the simultaneous optimization of the ascent trajectory of a two-stage launch vehicle and some significant vehicle design parameters. Besides the trajectory design, models are given that relate (i) the propulsion mass to a desirable increase in the mass flow for the rocket engines and (ii) the structural mass of the fuel tanks to a desirable increase in the propellant mass. Using these models, it is shown how the example vehicle should be modified in order to carry a higher payload into an Earth escape orbit. It is shown that an overall increase of the vehicle liftoff mass of about 4% will result in a payload increase of about 11%.
The author gratefully acknowledges the financial support provided by the European Space Technology Center (ESTEC) through its Contract Monitor Klaus Mehlem.
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References
Well, K. H., Markl, A., and Mehlem. K., ASTOS: A Trajectory Analysis and Optimization Software for Launch and Reentry Vehicles, Paper IAF-97-V4.04, 48th International Astronautical Congress, Turin, Italy, 1997.
Rahn, M., Schoettle, U. M., and Messerschmid, E., Multidisciplinary Design Tool for System and Mission Optimization of Launch Vehicles, 6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, Bellevue, Washington, USA, 1996.
Buhl, W., Ebert, K., and Wolff, H., Technical Report 2, Modelling: Advanced Launcher Trajectory Optimization Software Technical Documentation, European Space Technology and Research Center, Nordwijk, Netherlands, Contract 8046-88-NL-MAC, 1992.
Schöttle, U., and Rahn, U., Fahrzeugmodelle für Sensitivitätsstudien konventioneller Trägerraketen (Vehicle Modelling of Conventional Launch Vehicles for Sensitivity Analysis), Institute for Space Systems, University of Stuttgart, Stuttgart, Germany, Report IRS 95-IB-11, 1995 (in German).
Bock, H. G., and Plitt, K. J., A Multiple Shooting Algorithm for Direct Solution of Optimal Control Problems, Proceedings of the 9th IFAC World Congress, Budapest, Hungary, pp. 243–247, 1984.
Hargraves, C. R., and Paris, S. W., Direct Trajectory Optimization Using Nonlinear Programming and Collocation, Journal of Guidance, Control, and Dynamics, Vol. 10, pp. 338–342, 1987.
Kraft, D., TOMP-FORTRAN Modules for Optimal Control Calculations, VDI Fortschrittsberichte, Volume 8, No. 254, 1991.
Gill, P. E., Murray, W., and Saunders, M. E., Users Guide for SNOPT 5.3: A Fortran Package for Large-Scale Nonlinear Programming, Department of Mathematics, University of California, San Diego, Report NA 97-5-4, 1997.
Battin, R., Astronautical Guidance, McGraw-Hill, New York, NY, 1964.
Grimm, W., and Well, K. H., Guidance, Lecture Notes, Institute for Flight Mechanics and Control, University of Stuttgart, 1994 (in German).
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© 2004 Kluwer Academic Publishers
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Well, K.H. (2004). Neighboring Vehicle Design for a Two-Stage LaunchVehicle. In: Miele, A., Frediani, A. (eds) Advanced Design Problems in Aerospace Engineering. Mathematical Concepts in Science and Engineering, vol 48. Springer, Boston, MA. https://doi.org/10.1007/0-306-48637-7_5
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DOI: https://doi.org/10.1007/0-306-48637-7_5
Publisher Name: Springer, Boston, MA
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