Magnetic Multi-Pole Thruster Array With Shared Field Loops
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Solution Overview
Problem
Conventional plasma thrusters in satellite propulsion systems face challenges with high manufacturing costs, increased quality due to numerous elements, and limited service life, with enlarged designs compromising magnetic field control and thrust efficiency.
Innovation Solution
A magnetic multi-pole propulsion array system comprising multiple adjacent thrusters with shared magnetic components and a common magnetic field loop, allowing for adjustable scale and reduced weight and cost, while maintaining high thrust and durability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If the plasma thruster size is enlarged to increase service life, then the service life is improved, but the magnetic field strength is insufficient and plasma behavior becomes difficult to control
Solution Approach 1:
The invention divides the single plasma thruster into multiple smaller thrusters arranged in an array configuration. Each thruster maintains its own magnetic field components, allowing the system to achieve extended service life through redundancy while preserving adequate magnetic field strength in each individual unit. The segmented structure enables independent operation of multiple thrusters, ensuring that magnetic field control remains effective even as the overall system size increases.
2Reliability
If conventional plasma thruster elements are increased to improve plasma control, then plasma control is improved, but the manufacturing cost and quality increase
Solution Approach 1:
The invention merges multiple thruster units into a unified array system that shares common structural support and control infrastructure. By combining multiple simpler thruster modules rather than using a single complex thruster, the system achieves improved plasma control through collective operation while reducing overall device complexity and manufacturing cost compared to conventional single-thruster designs with numerous internal elements.
3Duration of action of stationary object
If the plasma thruster size is enlarged to increase service life, then the service life is improved, but the quality (weight) increases
Solution Approach 1:
The invention segments the thruster system into multiple smaller modular units arranged in an array, where each unit has reduced individual weight compared to a single large thruster. The total system weight is optimized by using multiple lightweight modules rather than one heavy unit, while the redundant configuration ensures extended service life through continued operation of remaining functional units even when others degrade or fail.
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
The system provides high thrust, low quality, and extended service life, with the ability to operate normally even with damaged thrusters or electron sources, reducing satellite mission risks and costs.
Implementation Method 1
The anode is disposed inside the discharge chamber and adapted to generate an electric field
Implementation Method 2
The plurality of magnetic components is respectively disposed on a plurality of sides of the discharge chamber
Data Source
AI summary
A magnetic multi-pole propulsion array system is applied to at least one external cathode and includes a plurality of magnetic multi-pole thrusters connected adjacent to each other. Each magnetic multi-pole thruster includes a propellant provider, a discharge chamber, an anode and a plurality of magnetic components. The propellant provider outputs propellant. The discharge chamber is connected with the propellant provider to accommodate the propellant. The anode is disposed inside the discharge chamber to generate an electric field. The plurality of magnetic components is respectively disposed on several sides of the discharge chamber. One of the several sides of the discharge chamber of the magnetic multi-pole thruster is applied for one side of a discharge chamber of another magnetic multi-pole thruster.