Ion Thruster with Sectored Extractor for Thrust Vectoring
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Solution Overview
Problem
Existing ion thrusters face challenges in achieving efficient and reliable thrust vectoring due to mechanical malfunctions, inefficiencies in propellant flow throttling, and mass inefficiencies, particularly in gimbal-mounted and plasma thruster systems.
Innovation Solution
The ion thruster controls the supply voltage of each sector independently to vary the electric field strength between the emitter and extractor, allowing precise thrust vectoring without inefficient throttling or mechanical moving parts, using a sectored extractor and emitter with symmetrical outlets to ensure accurate ion extraction and acceleration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If gimbal-mounting is used to control thrust vector orientation, then thrust direction control is achieved, but mechanical malfunction risk increases and reliability decreases
Solution Approach 1:
The patent replaces the mechanical gimbal mounting system with an electromagnetic control system. By dividing the extractor into sectors and applying independent voltages to each sector, the ion beam direction is controlled through electromagnetic forces rather than mechanical movement, eliminating gears, motors, and moving parts that cause mechanical failures.
Solution Approach 2:
The extractor is divided into multiple sectors (e.g., four quadrants) that can be independently controlled. By adjusting the voltage on each sector separately, the thrust vector can be directed in different directions without mechanical movement. This segmentation allows electronic control of thrust direction while maintaining a fixed, reliable structure.
2Ease of operation
If propellant flow throttling is used for thrust vectoring, then thrust direction control is achieved, but efficiency decreases and sudden collapse of ionization occurs
Solution Approach 1:
Instead of changing propellant flow rate to control thrust direction, the patent changes the electrical voltage parameter applied to different sectors of the extractor. By varying the voltage on each sector independently, the ion beam direction is controlled through electromagnetic field adjustments rather than propellant throttling, maintaining constant efficient propellant flow.
3Ease of operation
If mechanical valves are used for throttling propellant flow, then thrust vectoring is achieved, but device complexity increases and reliability decreases
Solution Approach 1:
The patent eliminates mechanical valves and throttling mechanisms by using electronic voltage control on sectorized extractor electrodes. This substitution of mechanical systems with electromagnetic control reduces device complexity, removes moving parts, and improves reliability while maintaining thrust vectoring capability.
4Ease of operation
If permanent inclination of ionization channels is used for thrust vectoring, then thrust direction control is achieved, but mass efficiency decreases
Solution Approach 1:
The patent makes the thrust vector direction dynamic and adjustable through electronic control of sector voltages, rather than using a fixed permanent inclination. The ionization channels remain straight and mass-efficient, while the electromagnetic fields dynamically steer the ion beam direction, allowing optimal mass efficiency with flexible direction control.
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 enables precise and reliable thrust vectoring with enhanced mass efficiency and reduced mechanical failures, as the electric field control allows for precise thrust direction without the need for propellant flow throttling or mechanical parts, ensuring consistent and controlled ion acceleration.
Implementation Method 1
Field-emission electric propulsion (FEEP) systems are based on field ionization of a liquid metal
Implementation Method 2
ions can be generated, e.g., from neutral gas (usually xenon) ionized by extracting electrons out of the atoms
Implementation Method 3
The ions extracted and accelerated by the extractor facing the emitter generate the thrust for propulsion of the spacecraft
Implementation Method 4
ions are accelerated by the electric field while the electrons are withheld by the magnetic field
Data Source
Figure 1a~1b
Figure 2a~2c
AI summary
The present invention relates to an ion thruster (1) for thrust vectored propulsion of a spacecraft, comprising a reservoir (2) for a propellant (3), an emitter (4) having a base (7) and, on one side (71) of the base (7), at least one outlet (8) for emitting ions (3+) of the propellant (3), wherein the base (7) is connected to the reservoir (2) for providing flow of propellant (3) from the reservoir (2) to said at least one outlet (8), and an extractor (5) facing said one side (71) of the emitter (4) for extracting and accelerating the ions (3+) from the emitter (4), wherein the extractor (5) is split into sectors (5i) about an axis (T) which orthogonally runs through said one side (71) of the emitter (4), wherein said sectors (5i) are electrically insulated from one another.