Liquid Propellant Pulsed Plasma Thruster for Miniaturization
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Solution Overview
Problem
Classical pulsed plasma thrusters have low efficiency and suffer from electrode erosion, limiting their thrust-to-power ratio and miniaturization potential for small satellites.
Innovation Solution
A plasma thruster device using an electrically insulating substrate with feed channels for an electrically conductive liquid to form a bridge structure, which is ionized by a current peak flow circuit, eliminating the need for a separate igniter and accelerator stage and preventing electrode erosion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If classical pulsed plasma thrusters use solid propellant (e.g., PTFE) with simple design, then reliability and miniaturization are improved, but thrust-to-power ratio is limited due to low efficiency
Solution Approach 1:
The patent changes the physical state of the propellant from solid to liquid, and introduces a dual-stage discharge process with specific timing parameters (ignition phase followed by main plasma phase). This parameter optimization enables efficient energy transfer and achieves high thrust-to-power ratio while maintaining the simplicity and reliability of the thruster design
Solution Approach 2:
The thruster employs periodic pulsed operation with two distinct phases within each cycle: an ignition phase that initiates plasma formation, and a main plasma phase that generates thrust. This periodic structured operation optimizes energy utilization and achieves high efficiency while maintaining system simplicity
2Power
If high power is applied to ionize solid propellant in classical PPT, then plasma generation is achieved, but electrode erosion occurs limiting lifetime
Solution Approach 1:
The patent uses liquid propellant (liquid metal or ionic liquid) that can be pumped and replenished through the discharge region. The liquid flow continuously replaces eroded material at the electrodes, preventing permanent damage and enabling indefinite operation. This hydraulic approach to propellant delivery solves the electrode erosion problem inherent in solid propellant systems
Solution Approach 2:
The liquid propellant system automatically replenishes itself at the electrode interfaces through continuous circulation. As material is consumed or eroded, fresh liquid propellant flows in to replace it, creating a self-healing system that maintains electrode integrity indefinitely without external intervention
3Speed
If two-stage process (ignition + acceleration) is used in advanced PPT, then plasma velocity is increased, but device complexity increases
Solution Approach 1:
The patent merges the ignition function and acceleration function into a single integrated discharge chamber and propellant delivery system. The dual-phase discharge process (ignition phase followed by main plasma phase) achieves both plasma formation and high velocity acceleration in one unified structure, eliminating the need for separate igniter and accelerator components
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 solution achieves a high thrust-to-power ratio and enables miniaturization by regenerating the electrodes, allowing for efficient and reliable operation in small satellites with improved propellant efficiency.
Implementation Method 1
forming a plasma of said electrically conductive liquid, when the electrically conductive liquid is ionized by a current peak flow circuit
Implementation Method 2
The application of this voltage causes a high, sharp-peaked current of several kA through the bridge structure that rapidly heats, melts, evaporates, and turns into plasma
Implementation Method 3
generates an electrical discharge through the formed low energy plasma, thereby generating a Lorentz force due to the interaction of a magnetic field and the electric discharge current through the plasma
Data Source
AI summary
In an aspect of the invention there is provided a plasma thruster device comprising: an electrically insulating substrate, said substrate comprising one or more feed channels for feeding an electrically conductive liquid to a bridge structure; said substrate further provided with electrical terminals; said bridge structure configured to form, when provided with the electrically conductive liquid, an electrical conducting bridge; said bridge structure configured to form contact areas in electrical contact with said electrical terminals, said bridge structure thereby connecting the contact areas, said bridge structure arranged for forming a plasma of said electrically conductive liquid, when the electrically conductive liquid is ionized by a current peak flow circuit that contacts the contact areas via said electrical terminals.