Numerical computation of orbit error covariance functions
| Autor: | Rama R. Kondapalli |
|---|---|
| Rok vydání: | 1996 |
| Předmět: |
Mathematical optimization
Covariance function Computer science Applied Mathematics Aerospace Engineering Covariance Numerical integration Estimation of covariance matrices Matérn covariance function Space and Planetary Science Control and Systems Engineering Applied mathematics Rational quadratic covariance function Satellite Astrophysics::Earth and Planetary Astrophysics Electrical and Electronic Engineering Orbit (control theory) |
| Zdroj: | Journal of Guidance, Control, and Dynamics. 19:245-246 |
| ISSN: | 1533-3884 0731-5090 |
| DOI: | 10.2514/3.21606 |
| Popis: | Introduction T RUNCATION of the Earth's gravitational field, when using a well-known low-degree model, and the uncertainty in the atmospheric drag parameters are two main force model errors that affect the ephemerides of low-altitude artificial satellites generated by numerical orbit propagation procedures. A statistical estimation of these orbit errors is very useful in defining an uncertainty ellipse of the region where a satellite would rise within the visibility circle of a tracking station. There exist some stochastic procedures to evaluate the order of magnitude of the accumulated global errors in short-term as well as in long-termorbit error propagations. The resulting orbit error covariance functions are bidimensional in nature, and a fast and accurate numerical quadrature is usually required for their evaluation. This work aims at determining a suitable quadrature for the evaluation of these double integrals. After explaining about various quadratures and their performance in some simple problems, results obtained from actual satellite data are presented. Orbit errors caused by numerical integrators have been dealt with elsewhere. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
|