Satellite Orbit Correction via Mathematical Function Approximation
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Solution Overview
Problem
Current satellite positioning systems face challenges in efficiently acquiring satellite signals due to lengthy processing times, which affects battery life in portable devices and increases network taxation, especially when dealing with extended satellite orbit data and frequent downloads of almanac and ephemeris data.
Innovation Solution
A method and system that compute corrections between coarse and precise satellite orbit data, approximating these corrections using mathematical functions to reduce the number of bits required for transmission, allowing mobile stations to efficiently determine satellite positions and timing with improved accuracy using an efficient messaging format.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If full precise orbit data is transmitted to mobile stations, then satellite position accuracy is improved, but message length and network taxation increase
Solution Approach 1:
The patent extracts only the essential correction terms from full precise orbit data that are necessary to improve satellite position accuracy. By identifying and transmitting only the critical correction parameters rather than complete orbit ephemeris, the message length is reduced while maintaining the accuracy improvement benefit.
Solution Approach 2:
The orbit correction data is segmented into multiple components including correction terms for satellite position, clock bias, and other parameters. This segmentation allows selective transmission of only the most critical correction terms needed for accurate position determination, reducing overall message length while preserving essential accuracy improvements.
2Measurement precision
If full precise orbit data is transmitted to mobile stations, then satellite position accuracy is improved, but network taxation increases
Solution Approach 1:
The patent extracts and transmits only the essential correction terms from complete orbit data. By removing redundant information and transmitting only the critical correction parameters needed for accurate satellite position determination, network taxation is reduced while maintaining the accuracy improvement benefit.
Solution Approach 2:
The orbit correction information is segmented into discrete correction terms for different parameters (position corrections, clock bias corrections, etc.). This segmentation enables selective transmission of only the most critical correction terms, reducing the quantity of data transmitted over the network while preserving essential accuracy improvements.
3Measurement precision
If extended SPS orbit information is used, then position determination accuracy is improved, but processing time increases
Solution Approach 1:
The patent extracts only the critical correction terms from extended orbit information that are necessary for improving position determination accuracy. By removing redundant data elements and transmitting only the essential correction parameters, processing time is reduced while maintaining the accuracy benefits of extended orbit information.
Solution Approach 2:
The extended orbit information is segmented into multiple correction terms for different parameters and time periods. This segmentation allows the mobile station to process only the relevant correction terms needed for current position determination, reducing overall processing time while preserving the accuracy improvements provided by extended orbit data.
Data Source
AI summary
A method and system for assisting mobile stations to locate a satellite use an efficient messaging format. A server computes a correction between coarse orbit data of a satellite and precise orbit data of the satellite. A coordinate system is chosen such that variation of the correction is substantially smooth over time. The server further approximates the correction with mathematical functions to reduce the number of bits necessary for transmission to a mobile station. The mobile station, upon receiving the coefficients, evaluates the mathematical functions using the coefficients and a time of applicability (e.g., the current time), converts the evaluated result to a standard coordinate system, and applies the conversion result to the coarse orbit data to obtain the precise orbit data.