Electrodeless Plasma Thruster with Closed-Ring Chamber
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Solution Overview
Problem
Current propulsion systems for spacecraft, particularly in Low Earth Orbit, face limitations such as limited maneuverability, high energy consumption, large mass and volume, and inefficiencies due to single thrust vector systems, which increase the risk of collisions and debris, and are unsuitable for small satellites requiring multi-directional thrust capabilities.
Innovation Solution
The development of electrodeless plasma thrusters with closed ring-shaped gas discharge chambers, which include a magnetic core antenna and power converter, allowing for multiple thrust vectors and reducing parasitic discharges, enabling efficient operation with reduced mass and power consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple conventional propulsion systems are incorporated into satellites to achieve multi-directional thrust, then maneuverability is improved, but weight increases and payload capacity decreases
Solution Approach 1:
The patent applies a single propulsion system that can generate thrust in multiple directions by varying the discharge chamber orientation and plasma flow direction, eliminating the need for multiple separate thrusters. This universal design provides omnidirectional maneuverability while maintaining low weight, directly resolving the contradiction between versatility and weight.
Solution Approach 2:
The patent combines multiple thrust vector capabilities into a single integrated propulsion unit with a configurable discharge chamber and magnetic nozzle system. By merging what would traditionally require multiple separate propulsion systems into one unified device, the patent achieves multi-directional control without the cumulative weight penalty of multiple independent thrusters.
2Adaptability or versatility
If multiple conventional propulsion systems are incorporated into satellites to achieve multi-directional thrust, then maneuverability is improved, but launch costs increase
Solution Approach 1:
The single multi-functional propulsion system replaces multiple specialized thrusters, reducing the total component count and system integration complexity. This universal design lowers launch costs by minimizing the number of systems that need to be installed, tested, and maintained on the satellite.
Solution Approach 2:
By consolidating multiple propulsion functions into one integrated unit with configurable thrust vectors, the patent reduces device complexity. The merged system requires fewer connection points, power distribution channels, and control systems compared to multiple independent thrusters, thereby reducing overall launch costs.
3Adaptability or versatility
If conventional propulsion systems are used to meet minimum satellite size requirements, then multi-directional thrust capability is achieved, but satellite size increases
Solution Approach 1:
The patent employs a single compact propulsion unit that provides omnidirectional thrust capability through configurable discharge chambers and magnetic nozzles. This universal design achieves multi-directional control without requiring the volume of multiple separate thrusters, maintaining small satellite size while providing full maneuverability.
Solution Approach 2:
The patent merges multiple thrust vector capabilities into one compact integrated propulsion system. By combining what would traditionally occupy multiple spatial locations into a single unified device with configurable orientation, the patent achieves multi-directional thrust without increasing satellite volume.
4Device complexity
If single thrust vector propulsion systems are used, then system simplicity is maintained, but maneuverability is limited and collision risk increases
Solution Approach 1:
The patent creates a single propulsion system that universally provides multi-directional thrust by configuring discharge chambers and magnetic nozzles in different orientations. This universal design maintains system simplicity with one integrated unit while achieving the maneuverability of multiple thrusters, eliminating collision risks without increasing complexity.
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 solution enhances spacecraft maneuverability, reduces mass and volume of propulsion systems, increases specific thrust and impulse, and extends thruster service life, making it suitable for small satellites and reducing the risk of collisions and debris.
Implementation Method 1
an antenna with a magnetic core (30) that creates an alternating magnetic field when a high frequency current is applied to it, which in turn creates an alternating electric field in the inner cavity of the gas discharge chamber (10)
Implementation Method 2
the propellant injected into the gas discharge chamber (10) is ionized due to the alternating electric field created by the antenna with a magnetic core (30)
Implementation Method 3
a closed ring-shaped gas discharge chamber (10) in which the propellant injected is ionized and creates plasma that flows along a closed-loop
Implementation Method 4
a first end of a guide tube (2) is connected to the gas discharge chamber (1), and a second end is open to outside space, wherein plasma flows from the gas discharge chamber (1) to the guide tube (2) in a direction from the inside to the outside
Data Source
AI summary
An electrodeless plasma thruster with closed-ring-shaped gas discharge chamber (1, 10) can include a gas discharge chamber (1, 10) closed-ring-shaped in fluid communication with a propellant storage system (10, 70). An antenna (3, 30) can be positioned on the exterior of the gas discharge tube (1, 10). A guide tube (2, 20) can be coupled with the gas discharge chamber (1, 10) at a first end and have a second open end. A magnetic system (7, 50) can be positioned on the second end of the guide tube (2, 20). The magnetic system (7, 50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11, 80) and a control module.