Hall Thruster Condensable Propellant Pressure Control
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Solution Overview
Problem
Conventional Hall thrusters using condensable propellants face challenges such as runaway vaporization and flow rate control issues, reliance on complex temperature regulation, electromagnetic pumps, and gravity for vaporization, leading to inefficiencies and high costs.
Innovation Solution
A Hall thruster design that decouples discharge current feedback from vaporization rate by controlling the pressure of condensable propellants using a pressure reducing device, eliminating the need for temperature regulation and electromagnetic pumps, and allowing for storage of both condensable and gaseous propellants in a single vessel, with a vaporizer at or above the vaporization temperature to maintain a controlled vaporization rate.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If temperature regulation is used to control vaporization rate, then vaporization can be controlled, but device complexity increases and anode melting occurs
Solution Approach 1:
The invention changes the control parameter from temperature to pressure. By using a pressure reducing device to control the pressure of condensable propellant supplied to the vaporizer, the system achieves vaporization rate control without the complexity and reliability issues of temperature regulation. The pressure control directly influences the vaporization rate through the relationship between pressure and vapor pressure of the propellant.
2Ease of operation
If electromagnetic pumps are used to control propellant flow rate, then flow rate control is achieved, but device complexity and cost increase
Solution Approach 1:
The invention replaces electromagnetic pumps with pressure control as the flow rate control mechanism. By regulating the pressure of condensable propellant using a pressure reducing device, the system achieves reliable flow rate control without requiring complex electromagnetic pump systems, thereby reducing device complexity and cost.
3Device complexity
If gravity-fed method is used for propellant delivery, then system is simple, but vaporization rate control is difficult and runaway condition occurs
Solution Approach 1:
The invention maintains the simplicity of the propellant delivery system by using gravity-fed method but adds pressure control as the regulating mechanism. The pressure reducing device controls the pressure of condensable propellant before it enters the vaporizer, preventing runaway vaporization conditions while keeping the overall system simple and reliable.
4Reliability
If separate storage vessels are used for condensable and gaseous propellants, then propellant storage is reliable, but device complexity increases
Solution Approach 1:
The invention combines the storage of condensable and gaseous propellants into a single storage vessel. This merging reduces device complexity by eliminating the need for separate storage systems while maintaining reliable propellant storage. The pressure control mechanism ensures that both types of propellants can be stored and delivered reliably from the same vessel.
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 design effectively regulates vaporization and flow rates, reduces complexity and cost, and enhances system efficiency by controlling propellant flow through pressure management, enabling stable operation and improved thrust performance.
Implementation Method 1
A condensable propellant flow controller includes a pressure reducing device for controlling the flow rate of the liquid condensable propellant
Implementation Method 2
A vaporizer at or above the vaporization temperature of the liquid condensable propellant vaporizes the liquid condensable propellant
Implementation Method 3
A vaporizer at or above the vaporization temperature of the liquid condensable propellant vaporizes the liquid condensable propellant
Implementation Method 4
A magnetic field source for establishing a transverse magnetic field in the plasma accelerator that creates an impedance to the flow of the electrons toward the anode
Implementation Method 5
accelerating ionized condensable propellant through the plasma accelerator to create a flux of ions
Data Source
AI summary
A Hall thruster for use with a condensable propellant including a plasma accelerator including an anode for providing plasma discharge, a distributor for distributing the condensable propellant in a liquid or vaporized state, and an electric circuit including a cathode for emitting electrons attracted to the anode and for neutralizing ion flux emitted from the plasma accelerator. A condensable propellant feed system includes a storage vessel for storing the condensable propellant and providing liquid condensable propellant at a controlled pressure. A condensable propellant flow controller includes a pressure reducing device for controlling the flow rate of the liquid condensable propellant. A vaporizer at or above the vaporization temperature of the liquid condensable propellant vaporizes the liquid condensable propellant at a predetermined vaporization rate and flow rate. A magnetic circuit structure includes a magnetic field source for establishing a transverse magnetic field in the plasma accelerator that creates an impedance to the flow of the electrons toward the anode to create plasma in the plasma accelerator for accelerating ionized condensable propellant through the plasma accelerator to create a flux of ions.