Satellite Orbit Data Verification via Position Comparison
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Solution Overview
Problem
Global navigational satellite systems (GNSS) face challenges in verifying the authenticity of received orbit data, which is crucial for accurate positioning and security applications, as disruptions or spoofing can lead to incorrect tracking and payment evasion.
Innovation Solution
A method and apparatus that calculate and compare satellite positions using received orbit data, employing an orbit propagation model accounting for gravitational bodies and solar pressure to determine the validity of the data, ensuring the accuracy and authenticity of the orbit information.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If orbit data is received and used for position calculation, then positioning functionality is enabled, but the risk of using spoofed or disrupted orbit data increases
Solution Approach 1:
The patent applies preliminary action by calculating a first position of the satellite at a first time using received orbit data before actually needing to verify the data. This advance calculation allows the system to model the orbit path and compare positions to detect spoofing attempts before they can compromise the positioning system, thereby preventing harmful effects rather than merely detecting them.
Solution Approach 2:
The patent implements feedback by comparing the modeled second position with the calculated third position derived from received orbit data. This comparison provides feedback on the validity of the orbit data, enabling the system to identify spoofed or disrupted signals and take corrective action, thus improving reliability while maintaining security against harmful factors.
2Measurement precision
If orbit propagation modeling is performed to verify satellite position, then data validity is improved, but computational complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the orbit verification process into distinct segments: calculating a first position at a first time, modeling the orbit path to determine a second position at a second time, and calculating a third position at the second time using received orbit data. This segmentation allows for systematic verification while managing computational complexity through structured, modular processing steps.
Solution Approach 2:
The patent uses partial action by performing orbit propagation modeling for only the specific time period needed for verification (from first time to second time) rather than modeling the entire orbit. This partial modeling approach achieves sufficient accuracy for validation while reducing unnecessary computational overhead and device complexity.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enhances the robustness of positional data signals by validating the orbit data, preventing disruptions and ensuring the accuracy of tracking and payment systems, thereby improving security and revenue collection in applications like vehicle tracking and electronic fee collection.
Implementation Method 1
The orbit propagation model may take into account the effects of at least one of: at least one gravitational body and solar pressure on the orbit path
Implementation Method 2
The orbit propagation model may take into account the effects of at least one of: at least one gravitational body and solar pressure on the orbit path
Data Source
AI summary
A first position of a satellite is calculated at a first time in dependence on received orbit data corresponding to an orbit path of the satellite. An orbit path of the satellite is modeled from the first position at the first time to a second time to determine a second position of the satellite at the second time. A third position of the satellite is then calculated at the second time in dependence on the received orbit data. The second position and third position are compared to determine a validity of the orbit data.