Satellite Trajectory Estimation Using Sequential Mode Correction
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Solution Overview
Problem
Current satellite trajectory correction methods are inefficient and time-consuming, requiring multiple iterations to achieve a predictable orbit due to uncertainties in thruster performance and environmental factors, and are hindered by the inaccessibility of thrusters for maintenance.
Innovation Solution
A computing system that uses a sequential mode of operation to determine and update the satellite's trajectory in real time by receiving data points from an uplink/downlink facility, calculating thruster performance, and iteratively refining the trajectory error using a bounded algorithm, allowing for real-time course corrections and thruster performance assessment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple iterations are used to determine satellite trajectory, then trajectory accuracy is improved, but time consumption increases
Solution Approach 1:
The patent applies preliminary action by performing a coarse trajectory determination before the thruster burn using available data, then performing a fine trajectory determination after the burn. This preliminary coarse estimation allows the system to quickly establish an initial trajectory without requiring multiple iterative measurements, thereby reducing time consumption while maintaining acceptable accuracy levels.
Solution Approach 2:
The patent implements feedback by using the actual satellite position data received after the thruster burn to update and refine the trajectory estimation. The system compares the expected trajectory with actual observations and uses this feedback to correct the trajectory model, achieving high accuracy with minimal iterations by leveraging real-time feedback from the uplink/downlink facility.
2Productivity
If real-time trajectory updates are performed, then maneuver efficiency is improved, but computational complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the trajectory determination into distinct phases: pre-burn trajectory determination, post-burn trajectory determination, and thruster performance calculation. Each phase processes specific data subsets and performs targeted calculations, reducing overall computational complexity while enabling real-time updates through modular, manageable computational tasks.
Solution Approach 2:
The patent uses partial action by calculating only the essential trajectory parameters and thruster performance metrics needed for maneuver efficiency, rather than performing complete orbital mechanics calculations. The system computes the minimum necessary updates to trajectory estimates based on received position data, achieving real-time efficiency without excessive computational burden.
Data Source
AI summary
A method for calculating a trajectory of a satellite following a maneuver includes determining a first estimated trajectory of a satellite using a first sequential mode of operation; performing a thruster burn as a correction maneuver for the satellite; and providing a real-time assessment of the correction maneuver by utilizing a second sequential mode of operation. The second sequential mode of operation includes receiving a data point from an uplink/downlink facility, determining a second estimated trajectory and an estimated thruster performance of the satellite based upon the received data point, and determining a trajectory error of the satellite based upon the received data point. The method further includes repeating the second sequential mode of operation if the trajectory error is above a specified threshold level, and repeating the first sequential mode of operation if the trajectory error is below the specified threshold level.