Variable Thrust Transfer Orbits for Electric Orbit Raising
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Solution Overview
Problem
Current electric orbit raising techniques for spacecraft, such as satellites, are inefficient in minimizing propellant usage and duration, as they rely on variable thrust control which is not optimized for power balance, leading to prolonged orbit raising times and potential propellant depletion for station-keeping.
Innovation Solution
The implementation of a control system with multidimensional optimizers and compound steering parameters to determine and execute optimized variable thrust transfer orbits, balancing electric power usage and propellant consumption, thereby minimizing electric orbit raising duration by optimizing the separation orbit and transfer orbits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of substance
If variable thrust control is used during electric orbit raising, then propellant consumption is reduced, but orbit raising duration is prolonged
Solution Approach 1:
The patent implements dynamic thrust adjustment by continuously varying the electric power supplied to thrusters during orbit raising maneuvers. The control system dynamically optimizes the balance between thrust magnitude and specific impulse, allowing the propulsion system to adapt its operating parameters in real-time based on the current orbital state and power availability, thereby resolving the contradiction between reduced propellant consumption and acceptable orbit raising duration.
Solution Approach 2:
The patent changes multiple operating parameters simultaneously including thrust level, specific impulse, and electric power consumption. By optimizing the combination of these parameters rather than controlling thrust alone, the system achieves more efficient propellant utilization while maintaining acceptable transfer times. This multi-parameter optimization approach allows the system to operate at optimal efficiency points that balance both duration and propellant usage.
2Duration of action of moving object
If electric power is increased to reduce orbit raising duration, then propellant usage is optimized, but power balance is disrupted
Solution Approach 1:
The patent incorporates feedback control mechanisms that continuously monitor the electric power balance between power generation (solar arrays) and power consumption (thrusters and onboard systems). The control system adjusts thrust commands based on real-time power availability, ensuring that orbit raising maneuvers do not disrupt the overall power balance. This feedback loop allows the system to optimize orbit raising duration while maintaining sustainable power consumption levels.
3Duration of action of moving object
If optimized variable thrust transfer orbits are implemented, then electric orbit raising duration is minimized, but system complexity increases
Solution Approach 1:
The patent divides the orbit raising process into multiple discrete transfer orbits, each optimized for specific operational requirements. By segmenting the overall transfer into manageable phases with distinct thrust and power characteristics, the control system can apply simplified optimization algorithms to each segment rather than attempting to optimize the entire trajectory simultaneously. This segmentation reduces computational complexity while achieving minimized total transfer duration.
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 significantly reduces the electric orbit raising duration by optimizing power balance and propellant usage, ensuring sufficient propellant reserves for station-keeping and improving overall mission efficiency.
Implementation Method 1
Thrusters are used during electric orbit raising to move the spacecraft from the initial injection orbit to the target orbit. The thrusters use a propellant. The amount of thrust generated by each thruster during firing is variable and is controlled by an amount of electric power supplied to the thruster.
Data Source
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AI summary
An apparatus for providing optimized power balanced variable thrust transfer orbits (402) to minimize an electric orbit raising duration is disclosed. The electric orbit raising includes a first transfer orbit (402) and a target orbit (408). The apparatus includes control electronics (140) configured to transfer to a second transfer orbit (402) to reach the target orbit (408). A variable thrust based on a current electric power balance is determined. The control electronics (140) are further configured to execute a maneuver to transfer from the first transfer orbit (402) to the second transfer orbit (408) according to the determined variable thrust and a predetermined maneuver plan (156). The predetermined maneuver plan (156) includes a set of compound steering parameters (158). The set of compound steering parameters (158) are based on an optimized variable thrust and an associated electrical power balance to the optimized variable thrust. An optimized series of transfer orbits minimizes the electric orbit raising duration.