Orbit propagation models

Overview of orbit propagation models

A few analytical orbit propagation models exist in CelestLab. All only consider the effect of gravity: central force and possibly a few zonal harmonic terms. Below is the complete list.

• Keplerian model (effect of central force)

  This is the most simple model, accounting only for the central attraction of the main body.

  The main asset of this model is that it can be used for elliptical and hyperbolic orbits.

• Secular J2 model (secular effects due to J2)

  This model only includes the secular effects on argument of perigee, right ascension of ascending node and mean anomaly due to J2. It is valid for elliptical (including circular) orbits only.

  The main asset (in comparison with more accurate models) is that the model can be used for any inclination (including near the critical inclination) and for equatorial orbits.

• Eckstein-Hechler model

  This model takes into account the effects of the zonal harmonics up to J6 (no tesseral term are considered).

  It is adapted to nearly circular orbits (eccentricity less than 0.05 and at most 0.1) and does not work for inclinations close to the critical inclinations (~63.43 deg and ~116.57 deg).

  The mean elements include secular and long-period effects.

  Note: The CelestLab version of the model includes a small adjustment to the mean eccentricity vector so that the eccentricity of a frozen orbit remains perfectly constant.

  References

  1) A reliable derivation of the perturbations due to any zonal and tesseral harmonics of the geopotential for nearly-circular satellite orbits, M. C. Eckstein, F. Hechler, ESRO SR-13-1970, ESA, Darmstadt, Germany, 1970.

  2) MSLIB FORTRAN 90, CNES, Volume E (me_eck_hech).

• Lyddane model

  This model, based on Brouwer theory modified by Lyddane, takes into account the effects of the zonal harmonics up to J5.

  It is useable for orbits with an eccentricity smaller than 0.9, and does not work for inclinations close to the critical inclinations (~63.43 deg and ~116.57 deg).

  There are 2 models derived from Lyddane in CelestLab:

  - The original Lyddane model for which the mean elements are orbital elements that vary secularly in time.

  - A second Lyddane model for which the mean elements include secular and long-period effects (the mean elements are then comparable with those defined by the Eckstein-Hechler model).

  References

  1) Solution of the problem of artificial satellite theory without drag, D. Brouwer, 1959, The Astronomical Journal - 64-1.

  2) Small eccentricities or inclinations in the Brouwer theory of artificial satellite motion, R.H. Lyddane, 1963, The Astronomical Journal - 68-8.

  3) MSLIB FORTRAN 90, CNES, Volume E (me_lyddane).