Conductive Liquid-Fed Pulsed Plasma Thrusters With Integrated Arc Ignition
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Solution Overview
Problem
Existing pulsed plasma thrusters (PPTs) face inefficiencies and reliability issues with solid, gaseous, and liquid propellants, particularly in small spacecraft, due to ablation, thermal damage, and complex injection systems, limiting their application in small spacecraft propulsion.
Innovation Solution
A conductive liquid-fed pulsed plasma thruster system with a first electrode having a conductive solid and liquid portion, a second electrode separated by an insulator, and a conductive liquid passage, where a drop of conductive liquid forms and ignites between the electrodes to generate a plasma cloud for thrust, eliminating the need for complex igniter systems and switching electronics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If solid propellants are used in pulsed plasma thrusters, then the thruster structure is simple, but thermal damage and ablation occur to the electrodes
Solution Approach 1:
The patent changes the physical state of the propellant from solid to liquid, which fundamentally alters how the propellant interacts with the electrodes. The liquid propellant can be pumped through channels and sprayed onto the electrode surface, allowing for controlled delivery and rapid evaporation without causing thermal damage or ablation to the electrode structure, thus resolving the contradiction between structural simplicity and thermal resistance
Solution Approach 2:
The patent utilizes the phase transition of the liquid propellant from liquid to vapor during combustion. The liquid propellant is delivered in liquid form through channels, then rapidly evaporates and combusts on the electrode surface, creating plasma. This phase transition allows the propellant to deliver energy without leaving solid residues that would cause ablation or thermal damage, solving the contradiction between simple structure and thermal harm
2Object-affected harmful factors
If liquid propellants are used in pulsed plasma thrusters, then thermal damage is reduced, but complex injection systems are required
Solution Approach 1:
The patent merges the propellant delivery function with the electrode structure itself. The liquid propellant channels are integrated directly into the electrode body, eliminating the need for separate injection systems. The electrode serves dual purposes: as the electrical component and as the propellant delivery mechanism, thus reducing overall system complexity while maintaining thermal damage reduction benefits
Solution Approach 2:
The electrode is designed to perform multiple functions simultaneously: electrical conduction, propellant delivery, and combustion chamber formation. By making the electrode multi-functional, the patent eliminates the need for separate injection systems that would otherwise be required for liquid propellant delivery, resolving the contradiction between reduced thermal damage and system complexity
3Power
If high discharge currents are used in pulsed plasma thrusters, then thrust is increased, but thermal electrode damage occurs
Solution Approach 1:
The patent changes the propellant state from solid to liquid, which allows for much higher discharge currents to be applied without causing thermal damage. The liquid propellant can be rapidly delivered and evaporated, enabling high-power pulses that generate increased thrust while the liquid nature of the propellant prevents the thermal accumulation that would damage solid electrodes, thus resolving the contradiction between thrust magnitude and thermal harm
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 achieves high efficiency and robust operation with simplified design, enabling reliable thrust generation in small spacecraft without thermal damage to electrodes and complex injection systems.
Implementation Method 1
a drop of the conductive liquid causes an arc discharge between the drop and the second electrode to ignite the drop and produce a plasma cloud that generates thrust when exhausted
Implementation Method 2
PPTs accelerate plasma propellant through the Lorentz-force-preferably with a minimum of thermal and electromagnetic loss
Implementation Method 3
produce a plasma cloud that generates thrust when exhausted
Data Source
AI summary
A conductive liquid-fed pulsed plasma thruster includes a first electrode having a conductive solid portion and a conductive liquid portion, a second electrode separated from the first electrode to define an ignition space therebetween, at least one electric insulator separating the first and second electrodes, and a conductive-liquid passage extending within the conductive solid portion through which the conductive liquid portion flows from an inlet to an outlet located at the ignition space. The first and second electrodes are configured so that a drop of the conductive liquid portion forms and grows at the outlet when the conductive liquid portion flows through the conductive liquid passage until the drop of the conductive liquid causes an arc discharge between the drop and the second electrode that ignites the drop to produce a plasma cloud that generates thrust when exhausted.