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4 - Elements of a Software System for Spacecraft Trajectory Optimization

Published online by Cambridge University Press:  06 December 2010

By
Cesar Ocampo
Edited by
Bruce A. Conway
Cesar Ocampo
Affiliation:
Department of Aerospace Engineering and Engineering Mechanics, The University of Texas at Austin, Austin, Texas
Bruce A. Conway
Affiliation:
University of Illinois, Urbana-Champaign
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Summary

Introduction

This chapter presents the main elements associated with a general spacecraft trajectory design and optimization software system. A unified framework is described that facilitates the modeling and optimization of spacecraft trajectories that may operate in complex gravitational force fields, use multiple propulsion systems, and involve multiple spacecraft. The ideas presented are simple and practical and are based in part on the existing wealth of knowledge documented in the open literature and the author's experience in developing software systems of this type.

The goal of any general trajectory design and optimization system is to facilitate the solution to a wide range of problems in a robust and efficient manner. A trade off exists between scope and depth. An attempt is made to strike a balance between the two and describe an approach that has proven to be robust and useful for a broad range of spacecraft trajectory design problems. The ideas and techniques presented here have been implemented in a working operational system known as Copernicus. This system has been used to support the detailed and comprehensive mission design studies associated with NASA's Constellation program. It has also been used to design and optimize the LCROSS mission trajectory which was launched on June 18, 2009.

Type
Chapter
Information
Spacecraft Trajectory Optimization , pp. 79 - 111
Publisher: Cambridge University Press
Print publication year: 2010

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References

[1] Ocampo, C. (2003) An Architecture for a Generalized Trajectory Design and Optimization System, in Libration Point Orbits and Applications, World Scientific, Publishing Co., Singapore.Google Scholar
[2] Ocampo, C. (2004) Finite Burn Maneuver Modeling for a Generalized Spacecraft Trajectory Design and Optimization System, Astrodynamics, Space Missions, and Chaos, Annals of the New York Academy of Sciences, Vol. 1017, p. 210–233CrossRefGoogle ScholarPubMed
[3] Williams, J. et. al. (2009) Global Performance Characterization of the Three Burn Trans-Earth Injection Maneuver Sequence over the Lunar Nodal Cycle, AAS09–380 Proceedings of the 2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA.
[4] Garn, M. et. al. (2008) NASA's Planned Return to the Moon: Global Access and Anytime Return Requirement Implications on the Lunar Orbit Insertion Burns, Proceedings of the 2008 AIAA Guidance, Navigation and Control Conference, Honolulu, HI.
[5] Lunar Crater Observation and Sensing Satellite (LCROSS) Official Website: http://lcross.arc.nasa.gov/
[6] Ranieri, C. L., Ocampo, C. (2009) Indirect Optimization of Three-Dimensional, Finite-Burning Interplanetary Transfers Including Spiral Dynamics, Journal of Guidance, Control, and Dynamics, Vol. 32, No. 2.CrossRefGoogle Scholar
[7] Leitmann, G. (1966) An Introduction to Optimal Control, McGraw-Hill, New York, NY.Google Scholar
[8] Bryson, A. E. Jr. and Ho, Y.C. (1975) Applied Optimal Control, Hemisphere Publishing Corporation, Revised Printing, New York, NY.Google Scholar
[9] Vincent, T.L. and Grantham, W.J. (1997) Nonlinear and Optimal Control Systems, John Wiley and Sons, New York, NY.Google Scholar
[10] Hull, D.G. (2003) Optimal Control Theory for Applications, Springer Verlag, New York, NY.CrossRefGoogle Scholar
[11] Pontryagin, L.S., et al. (1964) The Mathematical Theory of Optimal Processes, Pergamon Press, New York, NY.Google Scholar
[12] Lawden, D.E. (1963) Optimal Trajectories for Space Navigation, London Butterworths, London.Google Scholar
[13] Marec, J.P. (1979) Optimal Space Trajectories, Elsevier Scientific Publishing Company, New York, NY.Google Scholar
[14] ODEPACK: Serial Fortran Solvers for Initial Value Problems https://computation.llnl.gov/casc/odepack/odepack_home.html
[15] Dixon, L.C., Bartholomew-Biggs, M.C. (1981) Adjoint Control Transformations for Solving Practical Optimal Control Problems, Optimal Control Applications and Methods, 2, 365–381.CrossRefGoogle Scholar
[16] Dennis, J.E., Schnabel, R.B. (1983) Numerical Methods for Unconstrained Optimization and Nonlinear Equations, Prentice-Hall, Inc., Englewood Cliffs, NJ.Google Scholar
[17] Gill, P.E. et. al., (1998) Practical Optimization, Cambridge University Press, San Diego, CA.Google Scholar
[18] Zimmer, S., Ocampo, C. (2005) Use of Analytical Gradients to Calculate Optimal Gravity-Assist Trajectories, Journal of Guidance, Control, and Dynamics, 28, No. 2, 324–332.CrossRefGoogle Scholar
[19] Zimmer, S., Ocampo, C. (2005) Analytical Gradients for Gravity Assist Trajectories Using Constant Specific Impulse Engines, Journal of Guidance, Control, and Dynamics, 28, No. 4, 753–760.CrossRefGoogle Scholar
[20] Ocampo, C. et al. (2009) Variational Equations for a Generalized Trajectory Model, Proceedings of the AAS/AIAA Spaceflight Mechanics Conference, Savannah, GA.
[21] Harwell Subroutine Library (HSL) and Archive, http://www.cse.scitech.ac.uk/nag/hsl/
[22] Nocedal, J., Wright, S.J. (1999) Numerical Optimization, Springer-Verlag, New York, NY.CrossRefGoogle Scholar
[23] Stanford Business Software http://www.sbsi-sol-optimize.com/asp/sol_product_snopt.html
[24] Jesick, M., Ocampo, C. (2009) Automated Lunar Free-Return Trajectory Generation, Proceedings of the 19th AAS/AIAA Space Flight Mechanics Meeting, Savannah, GA.
[25] Lunar Reconnaissance Orbiter (LRO) Official Website: http://lro.gsfc.nasa.gov/
[26] Jesick, M., Ocampo, C. (2009) Lunar Orbit Insertion from a Fixed Free-Return, Proceedings of the 2009 AAS/AIAA Astrodynamics Specialist Conference, Pittsburgh, PA.
[27] Ocampo, C. et al. (2009) Initial Trajectory Model for a Multi-Maneuver Moon to Earth Abort Sequence, Proceedings of the 19th AAS/AIAA Space Flight Mechanics Meeting, Savannah, GA.

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