Satellite Thrust Balance Adjustment via Discharge Current Control
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Solution Overview
Problem
The existing orbit raising operations for artificial satellites are hindered by the accumulation of angular momentum in reaction wheels, which limits the duration of thruster firing and necessitates temporary suspension of orbit raising to release this momentum, thereby increasing the time required to reach a target orbit.
Innovation Solution
An artificial satellite equipped with a plurality of thrusters, an angular momentum detection apparatus, and a satellite controller that adjusts the thrust of specific thrusters based on detected angular momentum to maintain balance, preventing excessive accumulation in the reaction wheel.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If multiple electric thrusters simultaneously fire to perform orbit raising, then the orbit raising speed is improved, but angular momentum accumulates in the reaction wheel requiring periodic unloading which increases total time
Solution Approach 1:
The invention changes the operating parameters of individual thrusters by adjusting their discharge currents to compensate for thrust variations. The satellite controller monitors actual thrust deviations and modifies the discharge current of each thruster accordingly, transforming the system from fixed-parameter operation to adaptive parameter control, thereby eliminating angular momentum accumulation while maintaining continuous orbit raising
Solution Approach 2:
The invention implements a feedback control mechanism where the satellite controller continuously monitors the thrust output of each thruster, detects deviations from the target thrust, and adjusts the discharge current of affected thrusters in real-time. This closed-loop feedback system ensures that thrust variations are corrected dynamically, preventing angular momentum accumulation and enabling continuous uninterrupted orbit raising operations
2Reliability
If thruster thrust variations occur due to individual differences or distance variations from center of gravity, then angular momentum is generated, but the reaction wheel has limited capacity to absorb it
Solution Approach 1:
The invention performs preliminary thrust balance adjustment by proactively modifying the discharge currents of thrusters before angular momentum accumulation becomes problematic. The satellite controller calculates required current adjustments based on detected thrust variations and applies them in advance, preventing the buildup of angular momentum that would otherwise require reactive unloading operations
Solution Approach 2:
The invention compensates for individual thruster differences and position variations by dynamically adjusting the discharge current parameter of each thruster. This parameter modification equalizes the effective thrust contribution from each thruster, eliminating the root cause of angular momentum generation while maintaining simple reaction wheel operation
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 allows for continuous thruster operation, reducing the frequency of unloading and the time needed to achieve orbit by maintaining balanced thrust among thrusters, thus shortening the overall orbit raising process.
Implementation Method 1
an angular momentum detection apparatus to detect an angular momentum that is generated in the artificial satellite
Implementation Method 2
Each electric thruster ionizes xenon gas that is a propellant and accelerates the ionized xenon in a strong electric field, thereby obtaining a thrust as a reaction force
Implementation Method 3
Each electric thruster ionizes xenon gas that is a propellant and accelerates the ionized xenon in a strong electric field, thereby obtaining a thrust as a reaction force
Data Source
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AI summary
A reaction wheel (110) detects an angular momentum. A satellite controller (120) selects a target thruster based on the detected angular momentum. A power supply apparatus (130) changes adjustment electric power for the target thruster. A flow rate adjustment apparatus (140) supplies a propellant to the target thruster at a flow rate corresponding to the adjustment electric power. This changes a thrust of the target thruster. When a discharge current of the target thruster does not become a target current, the power supply apparatus further changes the adjustment electric power for the target thruster.