GNSS ephemeris with graceful degradation and measurement fusion
US9075140B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 23, 2010 |
| Grant date | Jul 7, 2015 |
| Priority date | — |
| Expiry date | Sep 2, 2032 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01S19/27
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
A method for providing an extended propagation ephemeris model for a satellite in Earth orbit, the method includes obtaining a satellite's orbital position over a first period of time, applying a least square estimation filter to determine coefficients defining osculating Keplarian orbital elements and harmonic perturbation parameters associated with a coordinate system defining an extended propagation ephemeris model that can be used to estimate the satellite's position during the first period, wherein the osculating Keplarian orbital elements include semi-major axis of the satellite (a), eccentricity of the satellite (e), inclination of the satellite (i), right ascension of ascending node of the satellite (Ω), true anomaly (θ*), and argument of periapsis (ω), applying the least square estimation filter to determine a dominant frequency of the true anomaly, and applying a Fourier transform to determine dominant frequencies of the harmonic perturbation parameters.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.