Authors

Abstract

In this research a perturbation based guidance method is developed for non-Keplerian problem. Problem is linearized in the presence non-gravitational forces like aerodynamic, so it can improve the performance of C* guidance for reentry problems. In this study developed method is used for a reentry guidance accuracy and performance. Results showed significant increases in accuracy compared to Keplerian approaches.

Keywords

[1] Battin, R. H., “Space Guidance Evelution – A Personal Narative”, Journal of Guidance, Control and Dynamics, Vol. 5, Issue 2, 1982, pp. 97-110.
[2] Battin, R. H., Astronautical Guidance, McGraw-Hill, New York, 1964.
[3] Battin, R. H., An Introduction to the Mathematics and  Methods of Astrodynamics, AIAA Education Series, New York, 1987.
[4] Laning, J. H. and Battin, R. H., “Interplanetary Navigation System Study”, NASA-N64-81342,1960.
[5] Battin, R. H., “A Comparison of Fixed and Variable Time of Arrival Navigation for Interplanetary Flight”, NASA-N64-83905, 1960.
[6] Tempelman, W. “Linear Guidance Laws for Space Missions”, Journal of Guidance, Control and Dynamics, Vol. 9, No. 4, 1986, pp. 495-502.
[7] DÁmario, L. A. and Edelbaum, T. N., “Minimum Impulse Three-Body Trajectory”, AIAA Journal, Vol.12, No. 4, 1974, pp. 455- 462.
[8] Zimmer, S., Ocampo, C., “Use of Analytical Gradients to Calculate Optimal Gravity Assist Trajectories”,Journal of Guidance, Control and Dynamics, Vol. 28,No. 2, 2005, pp. 324-332.
[9] Zimmer, S., Ocampo, C., “Analytical Gradients for Gravity Assist Trajectories Using Constant Specific Impulse Engines”, Journal of Guidance, Control and Dynamics, Vol. 28, No. 4, 2005, pp.753-760.
[10] Carter, T. E., “State Transition Matrices for Terminal Rendezvous Studies: Brief Survey and New Example”,Journal of Guidance, Control and Dynamics, Vol. 21,No. 1, 1998, pp. 148-155.
[11] Yamanaka, K., Ankersen, F., “New State Transition Matrix for Relative Motion on an Arbitrary Elliptical Orbit”, Journal of Guidance, Control and Dynamics,Vol. 25, No. 1, 2002, pp. 60-66.
[12] Gim, D. W., Alfriend, K. T., “State Transition Matrix of Relative Motion for the Perturbed Noncircular Reference Orbit”, Journal of Guidance, Control and Dynamics, Vol. 26, No. 6, 2003, pp. 956-971.
[13] Tsuda, Y., Scheeres, D. J., “State Transition Matrix Approximation Using a Generalized Averaging Method”, Journal of Guidance, Control and Dynamics, Vol. 32, No. 6, 2009, pp. 1781-1794.