Ion Accelerator Shielding Surface Erosion Reduction
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Solution Overview
Problem
The surface surrounding the exit opening of ion accelerator arrangements in spacecraft is prone to erosion due to the impact of ions from the ejected plasma jet, which can be severe and difficult to repair, especially in environments with high-energy cosmic radiation.
Innovation Solution
A magnetic field with a direction predominantly parallel to the surface section, combined with an electrically non-conductive or insulated shielding surface at a potential separate from the spacecraft's ground potential, effectively reduces ion impact by creating an electric field that repels further ions and deflects electrons, thereby minimizing erosion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a magnetic field with direction predominantly parallel to the surface section is introduced, then electron impact on the surface is reduced, but the device complexity increases
Solution Approach 1:
The magnetic field acts as an intermediary between the plasma jet and the surface section, deflecting electrons away from the surface before they can cause damage. The field mediates the interaction by introducing a third element (magnetic influence) that alters the trajectory of charged particles without direct physical contact.
Solution Approach 2:
The patent replaces potential mechanical shielding structures with a magnetic field-based solution. Instead of using physical barriers or absorptive materials to protect the surface, the invention uses electromagnetic forces to deflect electrons, substituting a mechanical approach with a field-based approach.
2Object-affected harmful factors
If the surface section is made electrically non-conductive or insulated, then positive charging is retained and ion repulsion is enhanced, but the ease of manufacture decreases
Solution Approach 1:
The patent changes the electrical parameter of the surface section from conductive to non-conductive or insulated. This parameter change allows the surface to retain positive charging capability, which in turn enables electrostatic repulsion of ions. The modification involves altering the electrical conductivity property rather than the physical structure.
Solution Approach 2:
By making the surface section electrically isolated, the patent creates an equipotential region that can maintain a stable positive charge. This isolated electrical state allows the surface to repel ions effectively without being short-circuited to the spacecraft body, maintaining the repulsive electric field.
3Object-affected harmful factors
If the magnetic field deflects electrons away from the surface, then electron-induced damage is reduced, but the manufacturing precision requirements increase
Solution Approach 1:
The magnetic field is configured to have local quality variations, with field strength and direction optimized specifically in the region near the surface section. The field is not uniformly distributed but rather tailored to provide maximum electron deflection precisely where needed, while allowing more flexibility in other regions.
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 configuration significantly reduces surface erosion by repelling positively charged ions and deflecting electrons, maintaining a repelling electric field and preventing electron impact on the shielding surface, thus protecting the spacecraft from plasma jet-induced damage.
Implementation Method 1
electrons which are accelerated by such a field in the direction of the surface section, due to their low mass and high speed are deflected in the magnetic field and kept away from the surface section
Implementation Method 2
a positive charging of the surface section resulting from an initial exposure of the surface section to ions leads to an electric field that repels further ions
Data Source
Figure 1~2
AI summary
The invention relates to a surface section that is exposed to an ion flow, in particular for a drive arrangement in a spacecraft, comprising an electrostatic ion accelerator arrangement. According to the invention, in order to reduce erosion, an intermediate potential energy surface is provided, said surface being advantageous in that it allows a magnetic field that is essentially parallel to the surface section to be formed.