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The main problem of artificial satellite theory for small and moderate eccentricities

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Abstract

Perturbation techniques based on Lie transforms as suggested by Deprit were used as the theoretical foundation for programming the analytical solution of the Main Problem in Satellite Theory (all gravitational harmonics being zero exceptJ 2). The collection of formulas necessary and sufficient to construct an ephemeris is given in the exposition. Short and long period displacements, as well as the secular terms, have been obtained up to the third order inJ 2 as power series of the eccentricity. They result from two successive completely canonical transformations which it has been found convenient not to compose into a unique transformation. Division by the eccentricity appears nowhere in the developments-neither explicitly nor implicitly. The determination of the constants of motion from the initial conditions has been given an elementary solution that is both complete and explicit without being iterative. The program was developed by Rom from MAO's package of subroutines forMechanizedAlgebraicOperations. Reliability tests have been run in two instances: in-track errors for ANNA 1B are only 20 cm after 210 days in orbit, while for RELAY II, they are 2.4 m, even after 350 days in orbit.

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Authors and Affiliations

  1. Boeing Scientific Research Laboratories, Seattle, Wash., USA

    André Deprit & Arnold Rom

Authors
  1. André Deprit
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  2. Arnold Rom
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Deprit, A., Rom, A. The main problem of artificial satellite theory for small and moderate eccentricities. Celestial Mechanics 2, 166–206 (1970). https://doi.org/10.1007/BF01229494

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  • DOI: https://doi.org/10.1007/BF01229494

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