Autonomous Electric Thruster Power Control for Orbit Raising
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current spacecraft thruster control systems during electric orbit raising are inefficient in minimizing propellant usage and duration, as they lack autonomous control over electric power distribution, leading to suboptimal thrust management and propellant conservation for station keeping.
Innovation Solution
A system and method for autonomously controlling electric power to thrusters on a spacecraft, using onboard processors to determine the state of charge of the battery and adjust electric power levels to match predefined operating points, optimizing thruster firing during sunlight and shutting off during eclipses to minimize propellant usage and duration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If electric power is increased to reduce orbit raising duration, then productivity improves, but propellant consumption increases
Solution Approach 1:
The system dynamically adjusts electric power levels to thrusters based on real-time battery state of charge measurements. Power levels are varied across different orbits and phases of the orbit raising process, transitioning from higher power when battery charge is sufficient to lower power when battery charge decreases, thereby optimizing the trade-off between orbit raising duration and propellant consumption
Solution Approach 2:
The invention changes the operating parameters of the thrusters by adjusting electric power levels according to predefined operating points that correspond to different battery state of charge thresholds. This parameter adjustment allows the system to operate at optimal efficiency points while responding to changing battery conditions, reducing overall propellant consumption while maintaining acceptable orbit raising duration
2Speed
If electric power is increased to maximize thrust, then speed improves, but use of energy increases
Solution Approach 1:
The system changes thruster operating parameters by selecting from multiple predefined operating points that correspond to different power levels. Each operating point represents an optimized balance between thrust output and power consumption, allowing the system to achieve necessary orbit raising speed while minimizing electric power draw from the battery
Solution Approach 2:
The thruster power levels are dynamically adjusted based on measured battery state of charge. The system transitions between different power levels during the orbit raising process, using higher power when battery charge is high and lower power when battery charge decreases, thereby optimizing the balance between orbit raising speed and energy consumption
3Ease of operation
If autonomous control is implemented to optimize power distribution, then ease of operation improves, but device complexity increases
Solution Approach 1:
The system performs self-service by autonomously measuring its own battery state of charge and automatically adjusting thruster power levels based on predefined operating points. The control electronics independently make decisions about power distribution without requiring external intervention, simplifying operation while the complexity is confined to the automated control logic
Solution Approach 2:
The system implements feedback control by continuously monitoring battery state of charge and using this information to adjust thruster power levels. The control electronics receive feedback from battery measurements and automatically modify operating parameters to maintain optimal performance, achieving ease of operation through automation
Data Source
AI summary
A method for autonomously controlling electric power supplied to a thruster of a spacecraft during electric orbit raising includes determining a state of charge of a battery onboard the spacecraft at an entry into an eclipse during each orbit of a plurality of orbits during the electric orbit raising of the spacecraft. The method also includes determining an electric power level used to fire each thruster of a plurality of thrusters during each orbit beginning after the eclipse, based at least on the state of charge of the battery, and that will provide a shortest electric orbit raising duration and minimize thruster propellant usage during electric orbit raising.