Modular Ion Thruster Layout to Prevent Electrode Leakage
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Solution Overview
Problem
Existing propulsion technologies for miniaturized satellites and small spacecraft are inefficient due to limited exhaust velocity, large and heavy fuel tanks, and complex electrical connections, making them unsuitable for adaptable and efficient thrust control.
Innovation Solution
An ion propulsion device with modular emission modules, a common extraction electrode, and a control unit that maximizes the number of emission modules while minimizing bulk, allowing for variable thrust and size adaptation, and preventing breakdowns and leakage currents through strategic electrode spacing and insulating support design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If chemical thrusters are used for propulsion, then thrust can be generated, but exhaust velocity is limited by the inherent specific energy released by combustion
Solution Approach 1:
The invention changes the fundamental propulsion mechanism from chemical combustion to electric field acceleration. By applying high voltage (several kilovolts) across the emission electrode and extraction electrode, ions are accelerated to much higher velocities than chemical thrusters can achieve, directly resolving the exhaust velocity limitation imposed by chemical energy density.
2Adaptability or versatility
If ion thrusters with multiple emission modules are used to increase thrust, then thrust control adaptability improves, but device complexity and bulk increase
Solution Approach 1:
The invention merges multiple emission modules into a single integrated structure where several emission electrodes are arranged in an array on one side of a single propellant reservoir, with a single extraction electrode on the opposite side. This consolidation reduces the number of separate electrical connections and control systems needed, thereby reducing device complexity while maintaining the ability to control thrust by adjusting the voltage applied to the electrode array.
Solution Approach 2:
The single extraction electrode serves all emission modules simultaneously, making it a universal component that extracts ions from multiple emission sites. This multi-functional design eliminates the need for separate extraction electrodes for each emission module, simplifying the overall device architecture while maintaining adaptable thrust control through voltage adjustment.
3Volume of moving object
If emission electrodes are placed closer together to reduce device size, then bulk is reduced, but breakdown and leakage currents occur
Solution Approach 1:
The invention introduces an insulating support structure as an intermediary between adjacent emission electrodes. This insulator prevents direct electrical contact and breakdown between electrodes while allowing the electrodes to be positioned close together for compactness. The insulating support acts as a mediator that enables close spacing without compromising electrical reliability.
4Weight of moving object
If propellant reservoir is made smaller to reduce weight, then weight is reduced, but operation duration is limited due to propellant depletion
Solution Approach 1:
The invention changes the state of the propellant from liquid to ionic form through ionization. By applying high voltage to the emission electrodes, neutral propellant molecules are ionized and then accelerated as ions. This parameter change allows the same mass of propellant to produce much higher exhaust velocities and longer operation durations, as ionized propellant can be continuously supplied and exhausted at high speeds without the limitations of liquid propellant storage and combustion.
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 device achieves efficient and adaptable thrust control with reduced bulk and cost, enabling prolonged operation and scalability for various spacecraft sizes, while maintaining electrical neutrality to prevent contamination and charge accumulation.
Implementation Method 1
each emission module is configured to emit an ion beam when an electric field is applied to the conductive liquid
Implementation Method 2
The charged particles are then accelerated at high speeds of the order of several tens of kilometres per second by the applied electric field
Implementation Method 3
This electric field deforms the liquid-propellant film into a conical structure referred to as a Taylor cone, located at the tip of the emitter, and extracts charged particles at the apex of the cone
Implementation Method 4
the at least one control unit is configured to control an emission current of the ions emitted by the application of a potential difference between at least one emission electrode and the extraction electrode
Implementation Method 5
a length L of the insulating support between the emission electrodes is greater than a propagation distance of an electric leakage current by hopping conduction along the insulating support between the emission electrodes
Data Source
AI summary
An ion propulsion device including emission modules in an emission plane, each module having an insulating support, an emission electrode on the support, and a conductive liquid with a microfluidic channel depositing conductive liquid on the electrode; an extraction electrode common to the emission modules and facing the modules; and a control unit, in which each module is configured to emit an ion beam when an electric field is applied to the liquid; each control unit controls an ion emission current emitted by applying a potential difference between each emission electrode and the extraction electrode; the emission electrodes are spaced apart by a linear distance that is greater than a distance between two adjacent emission electrodes separated by an empty space; and a length of the insulating support between the electrodes is greater than a propagation distance of an electric leakage current by charge jumping along the support between the electrodes.