Effect of atmospheric drag on artificial satellite orbits

The force per unit mass that the atmosphere exerts on an orbiting satellite can be modeled as (Batchelor 2000)

where is the mass density of the atmosphere (at the satellite's position), theThe density distribution of the terrestrial atmosphere is conveniently modeled as (de Pater and Lissauer 2010)

(10.131) |

Assuming that the atmospheric drag force, (10.130), is small compared to the force of gravitational attraction between the Earth and the satellite—and can, thus, be treated as a perturbation—the satellite's orbit can be modeled as Keplerian ellipse whose six elements evolve slowly in time under the influence of the drag. Let , , be cylindrical coordinates in a reference frame that is aligned with the satellite's instantaneous orbital plane, as described in Section I.1. Here, is the satellite's true anomaly. (See Section 4.11.) Making use of the analysis of Appendix I, we can write

(10.132) | ||

(10.133) | ||

(10.134) | ||

(10.135) | ||

(10.136) |

As has already been mentioned, the satellite's instantaneous orbit is a Keplerian ellipse characterized by six orbital elements, which we
choose to be the major radius, , the mean anomaly at epoch,
, the eccentricity, , the argument of the perigee, ,
the inclination (to the Earth's equatorial plane), , and the longitude of the ascending node (measured with respect to the vernal equinox),
.
(See Section 4.12.) These elements evolve slowly in time, under the influence of the atmospheric drag force. For the case in hand, this time evolution is most
conveniently specified in terms of the *Gauss planetary equations*, which take the form (see Appendix I)

(10.140) | ||

(10.141) | ||

(10.142) | ||

(10.143) | ||

(10.144) | ||

(10.145) |

(10.146) | ||

(10.147) |

As explained previously, we are working in the limit in which the atmospheric drag force is perturbative. This limit requires the relative changes in the satellite's orbital elements induced by the drag in an orbital period, , to all be small. It is apparent from Equations (10.148)–(10.151) that this is the case provided ; in other words, as long as the mass of air encountered by the satellite in a single orbit, which is , is much less than the satellite's mass. Assuming that we are in the perturbative limit (i.e., ), the evolution of the satellite's orbital elements takes place on a timescale that is much longer than its orbital period. We can concentrate on this evolution, and filter out any relatively short-term oscillations in the elements, by averaging expressions (10.148)–(10.151) over an orbital period. A suitable orbit-average operator is

(10.154) |

(10.159) |