Passive Igniter Pulse Circuit for Hall Thruster PPU Simplification

Solution Overview

Problem

The complex and costly power supply systems for Hall-effect electric thrusters, particularly the Power Processing Unit (PPU), increase the mass, volume, and reliability issues due to multiple power sources and electronic devices, making them inefficient and expensive.

Innovation Solution

A simplified electric power supply system using a passive electrical circuit with standard components like resistors and capacitors to generate pulses for igniter power, eliminating the need for complex electronic control and reducing the number of power sources, thereby improving ignition reliability and reducing costs.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If multiple power supply sources and electronic control devices are used to power the Hall-effect electric thruster, then the thruster can be powered, but the mass, volume, and cost increase

Engineering Contradiction:

Improveignition reliabilityVSAvoidPPU mass

Core Design Contradiction:

ReliabilityVSWeight of stationary object

Solution Approach 1:

The patent combines multiple power supply sources into a single power supply unit that can operate in different modes (ignition mode and support mode). The ignition module and support module are integrated into one unit, eliminating the need for separate power sources and reducing overall system mass while maintaining reliable ignition functionality.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The power supply unit is designed to perform multiple functions: it can provide high voltage for ignition, provide support power during the transition phase, and regulate power delivery to the cathode. This multi-functional design replaces what would traditionally require multiple specialized power sources, reducing mass and complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If multiple power supply sources and electronic control devices are used to power the Hall-effect electric thruster, then the thruster can be powered, but the volume increases

Engineering Contradiction:

Improveignition reliabilityVSAvoidPPU volume

Core Design Contradiction:

ReliabilityVSVolume of stationary object

Solution Approach 1:

The patent combines multiple power supply sources into a single power supply unit that can operate in different modes (ignition mode and support mode). The ignition module and support module are integrated into one unit, eliminating the need for separate power sources and reducing overall system mass while maintaining reliable ignition functionality.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The power supply unit is designed to perform multiple functions: it can provide high voltage for ignition, provide support power during the transition phase, and regulate power delivery to the cathode. This multi-functional design replaces what would traditionally require multiple specialized power sources, reducing mass and complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Reliability

If multiple power supply sources and electronic control devices are used to power the Hall-effect electric thruster, then the thruster can be powered, but the cost increases

Engineering Contradiction:

Improveignition reliabilityVSAvoidmanufacturing cost

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The patent combines multiple power supply sources into a single power supply unit that can operate in different modes (ignition mode and support mode). The ignition module and support module are integrated into one unit, eliminating the need for separate power sources and reducing overall system mass while maintaining reliable ignition functionality.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The power supply unit is designed to perform multiple functions: it can provide high voltage for ignition, provide support power during the transition phase, and regulate power delivery to the cathode. This multi-functional design replaces what would traditionally require multiple specialized power sources, reducing mass and complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

4Ease of operation

If multiple power supply sources and electronic control devices are used to power the Hall-effect electric thruster, then the thruster can be powered, but the reliability decreases due to more components

Engineering Contradiction:

Improveoperational complexityVSAvoidsystem reliability

Core Design Contradiction:

Ease of operationVSReliability

Solution Approach 1:

The patent combines multiple power supply sources into a single power supply unit that can operate in different modes (ignition mode and support mode). The ignition module and support module are integrated into one unit, eliminating the need for separate power sources and reducing overall system mass while maintaining reliable ignition functionality.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The power supply unit automatically transitions between ignition mode and support mode based on the operational state of the thruster. The electronic control sensor detects plasma generation and automatically switches modes without requiring complex external control systems, reducing operational complexity and improving reliability.

Inventive Principle:

Principle #25Self-service

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 solution provides a reliable and cost-effective power supply system that simplifies the ignition process, reduces the number of power sources, and enhances the efficiency of the Hall-effect electric thruster by using a passive electrical circuit to generate pulses, improving the thruster's operational reliability and reducing overall system mass and volume.

Implementation Method 1

a passive electrical circuit, powered by said third power supply source, and configured so as to generate a voltage in the form of at least one pulse

Methodology Applied

Scientific EffectCapacitance: Capacitance

Implementation Method 2

a second power supply source for supplying power to the heater 53 to heat the cathode 51

Methodology Applied

Scientific EffectJoule Heating: Joule Heating

Implementation Method 3

to enable it to emit electrons

Methodology Applied

Scientific EffectThermionic Emission: Thermionic Emission

Implementation Method 4

A propellant gas, usually xenon, is injected into the anode and collides with the electrons held there by a magnetic field

Methodology Applied

Scientific EffectMagnetic Field: Magnetic Field

Implementation Method 5

Hall-effect electric thruster

Methodology Applied

Scientific EffectHall Effect: Hall Effect

Implementation Method 6

An electronic control sensor detects this increase in current and then cuts off the ignition module 121

Methodology Applied

Scientific EffectElectrical Conductivity: Conduction (electrical)

Data Source

PatentUS10718319B2Electric power supply system for a hall effect electric thruster

Publication Date: 2020.07.21 AIRBUS DEFENCE & SPACE SAS

AI summary

An electric power supply system for a Hall effect electric thruster. The Hall effect electric thruster includes an anode, a cathode, a heater for the cathode and an igniter. The electric power supply system includes a first power supply source to power the anode, a second power supply source to power the heater and a power supply unit to electrically supply the igniter. The power supply unit includes a third power supply source and a passive electric circuit. The third power supply source powers the passive electric circuit and is configured to generate a voltage in the form of at least one pulse.