Converging Diverging Magnetic Nozzle for CubeSat Propulsion
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Solution Overview
Problem
Conventional electric propulsion systems for small satellites, such as CubeSATS, face challenges in miniaturization, requiring high propellant mass and power, and are inefficient at low power levels, limiting their ΔV capabilities and mission flexibility.
Innovation Solution
A magnetic nozzle system using permanent magnets to create a converging/diverging flow structure, similar to a de Laval nozzle, but employing magnetic fields to direct plasma flow, which converts thermal energy into kinetic energy, enabling efficient propulsion with low power consumption and compact design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If conventional electric propulsion systems are miniaturized for CubeSATS, then the satellite size and mass are reduced, but propellant mass requirements and power consumption increase
Solution Approach 1:
The patent replaces conventional chemical propulsion systems with an electric propulsion system that uses electromagnetic fields to accelerate plasma. This substitution eliminates the need for large amounts of chemical propellant while providing sufficient thrust for CubeSATS, directly resolving the contradiction between reduced satellite volume and reduced propellant mass requirements.
Solution Approach 2:
The invention changes the operating parameters by using low power consumption (less than 50 W) electric propulsion instead of high power chemical propulsion. This parameter change enables miniaturized satellites to achieve orbit insertion and maneuvers with significantly reduced propellant mass while maintaining acceptable performance levels.
2Volume of moving object
If conventional electric propulsion systems are miniaturized, then satellite size is reduced, but power consumption increases and efficiency decreases
Solution Approach 1:
The patent achieves low power consumption (less than 50 W) by optimizing the electric propulsion system parameters including plasma generation efficiency and magnetic field configuration. This resolves the contradiction by demonstrating that miniaturized electric propulsion can operate at low power levels with high efficiency, contrary to conventional systems that require high power for equivalent thrust.
3Weight of stationary object
If conventional electric propulsion is used, then satellite mass is reduced, but ΔV capability and mission flexibility are limited
Solution Approach 1:
The patent replaces chemical propulsion with electric propulsion using electromagnetic fields to accelerate plasma. This substitution provides continuous low-thrust capability that enables high ΔV maneuvers (greater than 1 km/s), allowing miniaturized satellites to perform diverse missions including orbit insertion, station-keeping, and formation flying, thereby resolving the contradiction between reduced mass and enhanced mission flexibility.
4Volume of moving object
If conventional electric thrusters are scaled down, then satellite size is reduced, but thrust effectiveness decreases
Solution Approach 1:
The patent achieves effective thrust from miniaturized thrusters by optimizing plasma generation parameters and magnetic field strength. The system produces sufficient thrust (0.5 to 4 mN) from a compact volume by efficiently converting electrical energy to kinetic energy of accelerated plasma, resolving the contradiction between reduced thruster size and maintained thrust effectiveness.
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 magnetic nozzle system achieves thrust levels of 0.5 to 4 mN and ΔV capabilities of 1-2 km/s, enabling more flexible satellite maneuvers and significant cost savings by allowing deployment of satellites into various orbits and configurations.
Implementation Method 1
a magnetic nozzle generated by permanent magnets uses the same converging/diverging contour shape to convert the thermal energy of a propellant into directed kinetic energy, but uses magnetic fields instead of a physical boundary to direct the flow of plasma
Implementation Method 2
uses magnetic fields instead of a physical boundary to direct the flow of plasma
Data Source
AI summary
A magnetic nozzle having a converging/diverging contour shape that converts the thermal energy of a propellant into directed kinetic energy, but uses magnetic fields instead of a physical boundary to direct the flow of particles.