Effects of force model errors on SEASAT satellite orbits
Abstract
Simulated SEASAT orbit data are generated under the influence of several perturbing forces. Least squares fits are made to the simulated data and the results are examined in relation to the feasibility of long arc (24 hours) ephemeris determination of SEASAT orbits. Perturbing forces considered are: (1) truncated earth's gravitation fields; (2) atmospheric drag; (3) solar radiation; (4) the earth's visible albedo. The orbit generation integration interval was also examined for truncation or round-off errors. Results indicate that the error build-up renders long arc SEASAT ephemeris determination infeasible at the orbit error level of one meter.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- May 1977
- Bibcode:
- 1977STIN...7732191B
- Keywords:
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- Orbital Mechanics;
- Scientific Satellites;
- Ephemerides;
- Gravitational Fields;
- Least Squares Method;
- Mathematical Models;
- Astrodynamics