A high-fidelity N-body ephemeris generator for satellites in Earth orbit

Details A high-fidelity N-body ephemeris generator for satellites in Earth orbit A high-fidelity N-body ephemeris generator for satellites in Earth orbit

Oct 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991asee.nasat....s&link_type=abstract

In Alabama Univ., Research Reports: 1991 NASA/ASEE Summer Faculty Fellowship Program 6 p (SEE N92-15850 06-80)

Other

Computer Programs, Earth Orbits, Ephemerides, Many Body Problem, Mission Planning, Structured Programming, Anomalies, Eccentricity, Lunar Effects, Perigees

Scientific paper

A program is currently used for mission planning called the Analytic Satellite Ephemeris Program (ASEP), which produces projected data for orbits that remain fairly close to Earth. Lunar and solar perturbations are taken into account in another program called GRAVE. This project is a revision of GRAVE which incorporates more flexible means of input for initial data, provides additional kinds of output information, and makes use of structured programming techniques to make the program more understandable and reliable. The computer program ORBIT was tested against tracking data for the first 313 days of operation of the CRRES satellite. A sample graph is given comparing the semi-major axis calculated by the program with the values supplied by NORAD. When calculated for points at which CRRES passes through the ascending node, the argument of perigee, the right ascension of the ascending node, and the mean anomaly all stay within about a degree of the corresponding values from NORAD; the inclination of the orbital plane is much closer. The program value of the eccentricity is in error by no more than 0.0002.

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