Coriolis forces in numerical integration of satellite orbits, and absolute reference system

Details Coriolis forces in numerical integration of satellite orbits, and absolute reference system Coriolis forces in numerical integration of satellite orbits, and absolute reference system

Dec 1974

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1974cemec..10..423b&link_type=abstract

Celestial Mechanics, vol. 10, Dec. 1974, p. 423-436.

Statistics

Applications

Coriolis Effect, Numerical Integration, Orbit Calculation, Satellite Orbits, Celestial Mechanics, Celestial Reference Systems, Classical Mechanics, Nutation, Orbital Elements, Precession

Scientific paper

The reference system defined by Veis and currently used for computing satellite orbits is not sufficiently accurate for some scientific applications, considering the new accuracy of laser data. Another orbital reference system with associated apparent forces is therefore defined. The reference system chosen is the mean celestial system 1970.0. The motion of a satellite is numerically integrated into the instantaneous celestial system (sidereal system), taking into account all the complementary forces due to precession and nutation. The complete set of formulas is given and has been introduced in a differential orbital improvement program.

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