Bi-modal Micro Cathode Arc Thruster for Satellite Propulsion
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Solution Overview
Problem
Existing micro-spacecraft propulsion systems, such as vacuum arc thrusters, are limited by fuel efficiency, thrust generation, and complexity, requiring new thrusters that can efficiently use fuel, vary thrust based on cathode material, and maintain a compact design for micro- and nano-satellites.
Innovation Solution
A micro-cathode arc thruster with alternating electrodes, where either the exterior or interior tubular electrode can function as a cathode, using a pulsed voltage source to create a plasma jet, and a magnetic field to direct thrust, allowing for efficient and adjustable propulsion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single cathode is used in the vacuum arc thruster, then the structure is simple, but the fuel is depleted quickly and the thruster lifetime is limited
Solution Approach 1:
The single cathode is segmented into multiple cathode segments (first cathode segment and second cathode segment) that can be independently depleted and replaced. This allows the thruster to continue operation by switching between segments, extending the overall lifetime without significantly increasing structural complexity.
Solution Approach 2:
As cathode material is depleted from one segment, the system switches to another segment with fresh cathode material. The depleted segment remains in place while a new segment is activated, allowing continuous operation without complete system replacement.
2Adaptability or versatility
If the cathode material is changed to vary thrust, then the propulsion capability is enhanced, but the fuel consumption increases
Solution Approach 1:
Different cathode segments are made from different materials (e.g., tungsten, molybdenum, graphite) with different ablation characteristics. By selecting which segment to activate, the system locally optimizes thrust production for specific mission requirements without wasting fuel through unnecessary material consumption.
Solution Approach 2:
The system dynamically switches between different cathode materials based on mission requirements, allowing adaptive thrust control. This dynamic selection enables the thruster to match propulsion needs with appropriate material properties, improving overall fuel efficiency.
3Force
If the thruster is designed for high thrust, then the propulsion capability is improved, but the system mass increases
Solution Approach 1:
The system changes operational parameters by selecting different cathode materials with different atomic masses and ablation rates. This allows the same physical thruster structure to produce varying thrust levels by changing the propellant material properties, rather than scaling the entire system mass.
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 thruster achieves efficient, low-thrust propulsion with adjustable thrust levels, extended lifetime, and reduced mass, suitable for micro- and nano-satellites, enabling precise attitude control and orbit maneuvers while minimizing system weight and power consumption.
Implementation Method 1
The switching device is switched to pulse voltage from the inductor to create an arc between the exterior electrode and the interior electrode
Implementation Method 2
Either the exterior electrode or the interior electrode serves as a cathode to generate a plasma jet through the thrust channel
Implementation Method 3
The plasma drive produces plasma about the external cathode-insulator interface, which is directed distally by the magnetic field
Data Source
AI summary
A thruster for a micro-satellite is disclosed. The thruster includes a voltage source, an inductor and a resistor. A switching device is coupled to the inductor and the resistor. The thruster includes an exterior electrode composed of a first propellant, an insulator located coaxially within the exterior electrode and an interior electrode composed of a second propellant located coaxially to the insulator and the exterior electrode. An exterior housing has a proximate end and an opposite distal end with a thrust channel. The exterior housing holds the exterior electrode, the insulator and the interior electrode. The switching device is coupled to either the exterior electrode or the interior electrode. The switching device is switched to pulse voltage from the inductor to create an arc between the exterior electrode and the interior electrode. Either the exterior electrode or the interior electrode may serve as a cathode to generate a plasma jet.