Self-Neutralizing Air-Breathing Plasma Thruster Drag Reduction
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Solution Overview
Problem
Air-breathing plasma thrusters face challenges in efficiently ionizing air in rarefied environments at low altitudes, leading to insufficient thrust and increased drag, particularly due to the need for collimators which complicate design and increase drag further.
Innovation Solution
A self-neutralizing air-breathing plasma thruster (SABPT) design that utilizes a low-power vacuum arc electron source to generate both positive and negative ions for beam neutralization, eliminating the need for external neutralizers and simplifying the ionization process by controlling electron energy and stability in harsh plasma environments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If collimators are used to increase air density for ionization, then ionization efficiency is improved, but drag increases and design complexity increases
Solution Approach 1:
The patent removes the collimator component from the system entirely. Instead of using a collimator to pre-compress air, the invention relies on the spacecraft's forward motion through the atmosphere to naturally compress air into the ionization chamber, eliminating the source of excessive drag while maintaining ionization capability.
Solution Approach 2:
Rather than compressing air before it enters the ionization chamber (collimator approach), the invention allows air to enter at atmospheric pressure and relies on the reverse process where the ionization chamber itself creates the necessary compression through the spacecraft's motion and chamber design.
2Productivity
If collimators are used to increase air density for ionization, then ionization efficiency is improved, but device complexity increases
Solution Approach 1:
The patent removes the collimator component from the system entirely. Instead of using a collimator to pre-compress air, the invention relies on the spacecraft's forward motion through the atmosphere to naturally compress air into the ionization chamber, eliminating the source of excessive drag while maintaining ionization capability.
Solution Approach 2:
The ionization chamber serves multiple functions: it acts as both the ionization region and the compression chamber. The spacecraft's forward motion provides the compression function that would otherwise require a separate collimator, simplifying the overall design while maintaining ionization efficiency.
3Stability of the object's composition
If external neutralizers are used for beam neutralization, then charge balance is improved, but device complexity increases
Solution Approach 1:
The patent combines the ionization function and neutralizer function into a single integrated system. The ionization chamber produces both positive ions and electrons, eliminating the need for a separate external neutralizer device. This merging reduces component count and system complexity while maintaining charge balance.
Solution Approach 2:
The ionization chamber serves itself by producing both the ions that need neutralization and the electrons that provide neutralization. This self-service approach eliminates the need for external neutralizer equipment, reducing system complexity while maintaining proper charge balance in the plasma beam.
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 SABPT achieves efficient air ionization and thrust generation without external neutralizers, reducing drag and enhancing mission duration by eliminating the complexity of collimators and propellant storage, while maintaining orbit stability through balanced thrust and drag compensation.
Implementation Method 1
a low-power vacuum arc electron source to generate both positive and negative ions
Implementation Method 2
utilizes a low-power vacuum arc electron source to generate both positive and negative ions for beam neutralization
Implementation Method 3
ABPT uses incoming air propellant that is ionized and then consequently accelerated to produce thrust
Data Source
AI summary
A plasma thruster has a tunable electron source configured to provide electrons with controllable energy. An entry electrode and an exit electrode permit an air flow to pass from the entry electrode to the exit electrode. The entry electrode and exit electrode receive electrons from the tunable electron source. A controller selectively controls the entry and exit electrodes to accelerate positive and negative ions in the air.