THE DERIVATION OF A SECOND-ORDER SATELLITE TRAJECTORY PREDICTOR IN TERMS OF GEOMETRICAL VARIABLES (paper presented at the 36th Congress of the International Astronautical Federation, Stockholm, Sweden, 7-12 October 1985)

Authors
  1. De Lafontaine, J.
Corporate Authors
Defence Research Establishment Ottawa, Ottawa ONT (CAN)
Abstract
The paper develops a new semianalytic theory by generalization of the Method of Averaging (MoA) and the Stroboscopic Method (SM). Unlike the traditional development of the MoA, which must use the mean anomaly, this new approach can treat any orbital anomaly. In particular, a more geometrically significant position variable, the true anomaly, is considered here. The extension of the traditional methods presents significant analytical and numerical advantages. For instance, the averaging of the rate functions does not require the usual change of variable to true anomaly and the evaluation of the short-period terms does not involve the solution of the transcendental Kepler equation. The new set of differential equations is completely independent of the satellite anomalistic motion, thus allowing the propagation of the state with a relatively large (up to a few days) integration stepsize.TRUNCATED
Date of publication
01 Jan 1986
Number of Pages
9
Reprinted from
Acta Astronautica, vol 13, no 8, 1986, p 481-489
DSTKIM No
87-00250
CANDIS No
49102
Format(s):
Hardcopy;Originator's fiche received by DSIS

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