Autonomous Satellite Orbit Control With Predictive Collision Avoidance
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Solution Overview
Problem
Existing autonomous orbit control systems for satellites in low Earth orbit face challenges in managing collision risks due to unpredictable orbital dynamics and lack of ground segment knowledge about onboard maneuvers, leading to frequent, small, and reactive corrections that are sensitive to variations in orbital dynamics and solar activity, and result in high sensitivity to perturbations.
Innovation Solution
A method for autonomous orbit control that integrates station-keeping and collision avoidance by calculating maneuver plans over a prediction horizon, using activation times to ensure the satellite's position and identify collision risks, adjusting maneuvers based on authorized slots and conjunction information to maintain a safe trajectory.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If autonomous orbit control is used with frequent small station-keeping maneuvers, then the satellite maintains its orbital position within a narrow window, but the control system becomes highly sensitive to variations in orbital dynamics and perturbations
Solution Approach 1:
The system determines a maneuver plan over a prediction horizon extending several orbits into the future, identifying and planning avoidance maneuvers in advance before conjunction events occur. This preliminary action allows the system to anticipate and prepare for potential collision risks rather than reacting to them in real-time, reducing sensitivity to unpredictable orbital perturbations
Solution Approach 2:
The system dynamically adjusts the maneuver plan based on updated conjunction information and orbital predictions. The prediction horizon is recalculated at each activation time, and the maneuver plan is modified to account for new conjunction data, solar activity variations, and orbital perturbations, making the system adaptive rather than static
2Speed
If the ground segment manages collision risks with reactive maneuvers, then the system responds to identified risks, but the reaction time is insufficient due to latency between ground and onboard systems
Solution Approach 1:
The autonomous orbit control system performs collision risk assessment and maneuver planning onboard the satellite without requiring ground segment intervention. The system independently determines maneuver plans, evaluates conjunction risks, and executes avoidance maneuvers autonomously, eliminating ground-to-satellite communication latency and enabling immediate response to collision threats
Solution Approach 2:
The system continuously determines maneuver plans over a prediction horizon several orbits into the future, identifying potential collision risks in advance. By planning avoidance maneuvers before conjunction events occur and before ground segment involvement would be needed, the system eliminates reaction time delays associated with ground-based risk management
3Productivity
If autonomous orbit control operates with short lead times, then maneuvers can be executed quickly, but the ground segment cannot take the maneuver plan into account and precise future trajectory is unknown
Solution Approach 1:
The system determines a complete maneuver plan over a prediction horizon extending several orbits into the future at each activation time. This preliminary planning provides the ground segment with advance knowledge of the satellite's future trajectory and planned maneuvers, allowing the ground to anticipate and coordinate with onboard actions while maintaining autonomous execution efficiency
Solution Approach 2:
The system provides feedback to the ground segment by transmitting the determined maneuver plan and prediction horizon information. This feedback loop allows the ground segment to receive and process future trajectory information, improving situational awareness and coordination while the autonomous system maintains its ability to execute maneuvers efficiently with appropriate lead time
Data Source
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AI summary
The invention relates to a method (100) for controlling the orbit of a satellite, which method comprises: - determining (102) a manoeuvre plan (PMA) comprising at least one previous manoeuvre (PM1) of the previous manoeuvre plan (PPMA), if the at least one previous manoeuvre (PM1 = MA1) is implemented on a date corresponding to a previous fixed part (PPF) and the prediction horizon (HP), the manoeuvre plan (PMA) comprising at least one manoeuvre (MA2, MA3) implemented during a part of the prediction horizon; - identifying (103) a collision risk; - determining (104) a new manoeuvre plan (NPMA) comprising a previous manoeuvre (PM1, PM2, PM3) of the previous manoeuvre plan (PPMA), if the previous manoeuvre is implemented within the previous prediction horizon (PHP) and the prediction horizon (HP) of the new manoeuvre plan (NPMA), and comprising a new manoeuvre (NMA4), implemented over a new part of the prediction horizon (HP).