Simulation of precise orbit determination for a lunar orbiter

Details Simulation of precise orbit determination for a lunar orbiter Simulation of precise orbit determination for a lunar orbiter

Apr 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005acasn..46..186h&link_type=abstract

Acta Astronomica Sinica, vol. 46, no. 2, p. 186-195

Astronomy and Astrophysics

Astronomy

4

Celestial Mechanics Lunar Exploration, Precise Orbit Determination, Lunar Gravity

Scientific paper

The precision of orbit determination for the on-going Chinese lunar exploration mission `Chang Er 1', using the joint tracking network of United S-Band (USB) and Very Long Baseline Interferometry (VLBI) with real network geographic distribution scenario is studied is studied. The 3-step strategy of data simulation with errors, orbit determination and orbital comparison is adopted. The tool used is a space data analysis software package GEODYN developed at Goddard Space Flight Center, NASA. The leading error source for a lunar orbiter, i.e., the lunar gravity, is studied for the state-of-the-art model of JGL165P1. Two-way ranging, ranging rate as well as VLBI delay, delay-rate are simulated with GEODYN. The orbit determination is performed with a gravity model differing with the nominal JGL165Pl by its formal uncertainty. The reduced dynamics method is used to absorb orbital errors produced by the gravity error, in which a set of empirical acceleration parameters are estimated along with the initial state vector. It is conclude that for the lunar missions not aiming at improving lunar gravity, such as the `Chang Er 1', the reduced dynamic method of orbit determination is effective in absorbing gravity errors.

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