Spacecraft Ion Drive Voltage Supply Simplification
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Solution Overview
Problem
Conventional ion drives for spacecraft are complex and costly due to their electronic assemblies, which complicate the voltage supply system and reduce operational reliability and increase control effort.
Innovation Solution
An ion drive design that derives the necessary high voltages for ion acceleration and neutralization from the currents and voltages generated by a high-frequency generator, simplifying the voltage supply system and potentially eliminating the need for a separate neutralizer by using a high-voltage transformer and rectification/smoothing networks to optimize voltage and phase for the acceleration system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a separate electron source and plasma coupling system are used to neutralize the ion beam, then the ion drive can maintain charge balance, but the device complexity and electronic assembly requirements increase
Solution Approach 1:
The patent combines the electron source and plasma coupling system into an integrated neutralizer assembly that works in conjunction with the acceleration grids. The neutralizer is positioned downstream of the acceleration section and shares structural and electrical integration with the existing grid system, reducing the need for separate electronic assemblies while maintaining charge balance functionality.
2Force
If conventional grid systems with multiple voltage sources are used for ion acceleration, then thrust generation is achieved, but the voltage supply system becomes complex and control effort increases
Solution Approach 1:
The patent implements a multi-functional voltage supply system where a single high-voltage source serves multiple purposes: it provides acceleration voltage to the ion beams, generates the electromagnetic field for electron emission in the neutralizer, and maintains plasma confinement. This eliminates the need for separate voltage sources for each function, simplifying the overall voltage supply architecture while maintaining thrust generation capability.
Solution Approach 2:
The patent utilizes time-varying voltage parameters applied to the acceleration grids, where the voltage magnitude and polarity are modulated according to the oscillating electromagnetic field frequency. This dynamic parameter control enables a single voltage source to perform multiple functions throughout the oscillation cycle, reducing system complexity while maintaining effective ion acceleration.
3Productivity
If multiple separate components (gas supply, HF generator, voltage sources) are used to operate the ion drive, then the engine can function properly, but the structural complexity increases
Solution Approach 1:
The patent integrates the gas supply system, HF generator, and voltage supply into a unified operational architecture where components share common structural support, power distribution, and control systems. The discharge chamber serves as both the ionization region and part of the acceleration structure, while the neutralizer assembly is electrically integrated with the main power system, reducing the number of separate structural elements required.
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 design reduces the mass of the ion drive, increases operational reliability, and minimizes control effort by simplifying the structural design and eliminating the need for a separate neutralizer, while ensuring equivalent ion and electron currents.
Implementation Method 1
a high-frequency generator for generating an alternating electromagnetic field for the ionization of a propellant
Implementation Method 2
generating an alternating electromagnetic field for the ionization of a propellant
Implementation Method 3
a system for accelerating the generated charge carriers
Data Source
AI summary
An ion drive for a spacecraft, including a high-frequency generator for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system for the charge carriers, is provided. The ion drive includes a voltage source with which the high voltages that are necessary for the acceleration system can be derived from the currents and/or voltages generated by the high-frequency generator for generating the alternating electromagnetic field.