Abstract
In this paper, a systematic study of the optimization of trajectories for Earth-Moon flight is presented. The optimization criterion is the total characteristic velocity and the parameters to be optimized are: the initial phase angle of the spacecraft with respect to Earth, flight time, and velocity impulses at departure and arrival. The problem is formulated using a simplified version of the restricted three-body model and is solved using the sequential gradient-restoration algorithm for mathematical programming problems.
For given initial conditions, corresponding to a counterclockwise circular low Earth orbit at Space Station altitude, the optimization problem is solved for given final conditions, corresponding to either a clockwise or counterclockwise circular low Moon orbit at different altitudes. Then, the same problem is studied for the Moon-Earth return flight with the same boundary conditions.
The results show that the flight time obtained for the optimal trajectories (about 4.5 days) is larger than that of the Apollo missions (2.5 to 3.2 days). In light of these results, a further parametric study is performed. For given initial and final conditions, the transfer problem is solved again for fixed flight time smaller or larger than the optimal time.
The results show that, if the prescribed flight time is within one day of the optimal time, the penalty in characteristic velocity is relatively small. For larger time deviations, the penalty in characteristic velocity becomes more severe. In particular, if the flight time is greater than the optimal time by more than two days, no feasible trajectory exists for the given boundary conditions.
The most interesting finding is that the optimal Earth-Moon and Moon-Earth trajectories are mirror images of one another with respect to the Earth-Moon axis. This result extends to optimal trajectories the theorem of image trajectories formulated by Miele for feasible trajectories in 1960.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
Miele, A., Theorem of Image Trajectories in the Earth-Moon Space, Astronautica Acta, Vol. 6, No. 5, pp. 225–232, 1960.
Mickelwait, A. B., and Booton, R. C., Analytical and Numerical Studies of Three-Dimensional Trajectories to the Moon, Journal of the Aerospace Sciences, Vol. 27, No. 8, pp. 561–573, 1960.
Clarke, V. C., Design of Lunar and Interplanetary Ascent Trajectories, AIAA Journal, Vol. 5, No. 7, pp. 1559–1567, 1963.
Reich, H., General Characteristics of the Launch Window for Orbital Launch to the Moon, Celestial Mechanics and Astrodynamics, Edited by V. G. Szebehely, Vol. 14, pp. 341–375, 1964.
Dallas, C. S., Moon-to-Earth Trajectories, Celestial Mechanics and Astrodynamics, Edited by V. G. Szebehely, Vol. 14, pp. 391–438, 1964.
Bazhinov, I. K., Analysis of Flight Trajectories to Moon, Mars, and Venus, Post-Apollo Space Exploration, Edited by F. Narin, Advances in the Astronautical Sciences, Vol. 20, pp. 1173–1188, 1966.
Shaikh, N. A., A New Perturbation Method for Computing Earth-Moon Trajectories, Astronautica Acta, Vol. 12, No. 3, pp. 207–211, 1966.
Rosenbaum, R., Willwerth, A. C., and Chuck, W., Powered Flight Trajectory Optimization for Lunar and Interplanetary Transfer, Astronautica Acta, Vol. 12, No. 2, pp. 159–168, 1966.
Miner, W. E., and Andrus, J. F., Necessary Conditions for Optimal Lunar Trajectories with Discontinuous State Variables and Intermediate Point Constraints, AIAA Journal, Vol. 6, No. 11, pp. 2154–2159, 1968.
D’Amario, L. A., and Edelbaum, T. N., Minimum Impulse Three-Body Trajectories, AIAA Journal, Vol. 12, No. 4, pp. 455–462, 1974.
Pu, C. L., and Edelbaum, T. N., Four-Body Trajectory Optimization, AIAA Journal, Vol. 13, No. 3, pp. 333–336, 1975.
Kluever, C. A., and Pierson, B. L., Optimal Low-Thrust Earth-Moon Transfers with a Switching Function Structure, Journal of the Astronautical Sciences, Vol. 42, No. 3, pp. 269–283, 1994.
Rivas, M. L., and Pierson, B. L., Dynamic Boundary Evaluation Method for Approximate Optimal Lunar Trajectories, Journal of Guidance, Control, and Dynamics, Vol. 19, No. 4, pp. 976–978, 1996.
Kluever, C. A., and Pierson, B. L., Optimal Earth-Moon Trajectories Using Nuclear Electric Propulsion, Journal of Guidance, Control, and Dynamics, Vol. 20, No. 2, pp. 239–245, 1997.
Kluever, C. A., Optimal Earth-Moon Trajectories Using Combined Chemical-Electric Propulsion, Journal of Guidance, Control, and Dynamics, Vol. 20, No. 2, pp. 253–258, 1997.
Miele, A., Huang, H. Y., and Heideman, J. C., Sequential Gradient-Restoration Algorithm for the Minimization of Constrained Functions: Ordinary and Conjugate Gradient Versions, Journal of Optimization Theory and Applications, Vol. 4, No. 4, pp. 213–243, 1969.
Miele, A., Naqvi, S., Levy, A. V., and Iyer, R. R., Numerical Solutions of Nonlinear Equations and Nonlinear Two-Point Boundary-Value Problems, Advances in Control Systems, Edited by C. T. Leondes, Academic Press, New York, New York, Vol. 8, pp. 189–215, 1971.
Miele, A. and Mancuso, S., Optimal Trajectories for Earth-Moon-Earth Flight, Aero-Astronautics Report 295, Rice University, 1998.
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2004 Kluwer Academic Publishers
About this paper
Cite this paper
Miele, A., Mancuso, S. (2004). Design of Moon Missions. 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_2
Download citation
DOI: https://doi.org/10.1007/0-306-48637-7_2
Publisher Name: Springer, Boston, MA
Print ISBN: 978-0-306-48463-6
Online ISBN: 978-0-306-48637-1
eBook Packages: Springer Book Archive