Abstract
For a precise interplanetary orbit, the n-body problem including the sun and the nearby planets must be solved. However, for a preliminary analysis the method of patched-conics based on three distinct two-body problems is generally satisfactory. The orbit will then consist of a planetocentric segment near the departure planet, a heliocentric segment, and a final planetocentric segment near the destination planet. In this discussion we will be concerned mainly with the third phase dealing with the dynamics of planetary approach. In particular we will consider the Earth-Mars journey, in which case the approach trajectory is computed on the two-body Spacecraft-Mars assumption.
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References
“Trajectory Selection Considerations for Voyager Mission to Mars During 1971–72”. Jet Propulsion Lab., Pasadena, Calif. Document No. 281, Sept. 15, 1965.
Private Communications with E. Kane Casani, Jet Propulsion Lab.
Thomson, W. T.: Introduction to Space Dynamics, John Wiley & Sons, New York, 1961, Chapter 4.
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© 1968 Springer Science+Business Media New York
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Thomson, W.T. (1968). Dynamics of Planetary Approach. In: Loh, W.H.T. (eds) Re-entry and Planetary Entry Physics and Technology. Applied Physics and Engineering, vol 3. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-50082-4_7
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DOI: https://doi.org/10.1007/978-3-642-50082-4_7
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-50084-8
Online ISBN: 978-3-642-50082-4
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