Satellite Antenna Tracking with Kalman-Filtered Three-Point Peaking
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Solution Overview
Problem
Existing satellite tracking systems face challenges in maintaining precise alignment with geostationary satellites due to external forces and signal fluctuations, leading to excessive antenna wear and unreliable signal tracking, especially during precipitation and atmospheric scintillations.
Innovation Solution
A method and apparatus that utilize a three-point peaking technique to determine the optimal antenna orientation by measuring signal levels at three angles, calculating quadratic coefficients, and applying a Kalman filter to estimate and predict satellite positions, reducing the need for frequent antenna adjustments and improving tracking accuracy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If step tracking techniques are used to maximize signal strength by executing series of steps in azimuth and elevation, then signal reception is improved, but excessive wear of the drive system occurs due to many back-and-forth motions
Solution Approach 1:
The system performs preliminary action by predicting satellite position based on orbital parameters before actual tracking is needed. The earth station antenna is pre-positioned according to calculated orbital elements, eliminating the need for frequent back-and-forth scanning motions and reducing drive system wear while maintaining accurate signal reception.
Solution Approach 2:
The patent replaces the mechanical step-tracking system with an orbital mechanics-based prediction system. Instead of mechanically scanning through azimuth and elevation steps to find the satellite, the system uses Kepler's laws and orbital parameter calculations to determine antenna positioning, substituting computational mechanics for mechanical search motions.
2Device complexity
If conventional peaking techniques are used that compare each measurement only with the immediately precedent measurement, then the process is simple, but the technique is unreliable in the presence of severe atmospheric scintillations or precipitation attenuation
Solution Approach 1:
The system implements feedback by continuously monitoring received signal strength and using this information to refine orbital parameter estimates. The measured signal levels are fed back into the tracking algorithm to correct predicted positions, creating a closed-loop system that adapts to actual conditions rather than relying solely on open-loop predictions.
Solution Approach 2:
The system performs preliminary estimation of satellite position using orbital parameters before actual signal measurement is required. This preliminary positioning allows the system to be prepared in advance and makes fewer adjustments during adverse conditions, reducing the impact of signal fluctuations on tracking reliability.
3Power
If the antenna beamwidth is reduced to increase gain, then signal gain is improved, but it becomes necessary for the earth station antenna to track the apparent satellite motion to avoid large variations in received signal strength
Solution Approach 1:
The patent replaces complex mechanical tracking systems with an orbital mechanics-based prediction system. By using Kepler's laws and orbital parameter calculations, the system determines antenna positioning computationally rather than through complex mechanical scanning mechanisms, reducing tracking system complexity while maintaining precise alignment with narrow-beam high-gain antennas.
Data Source
AI summary
A satellite tracking system and method, a three-point peaking technique is used to determine the direction of a satellite 50 which includes a signal source. A Kalman filter is used to minimize the effects of noise in the received signal during the three-point peaking operation. This determination may be made at any time. Once the position of a satellite 50 has been determined twice over a time interval, its future position may be estimated by an adaptive continuous step track technique, using a Kalman filter, which assumes that the satellite moves uniformly with time as viewed from the antenna.