Hall Thruster Igniter Pulse Circuit for Simpler Power Supply
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Solution Overview
Problem
The power supply systems for electric Hall effect thrusters are complex, costly, and voluminous due to multiple power sources and electronic control sensors, which affects reliability and increases the mass of the thruster.
Innovation Solution
A passive electrical circuit comprising conventional components like resistors, diodes, and capacitors generates pulses to simplify the power supply for the igniter, eliminating the need for external control and reducing mass and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple power sources and electronic control sensors are used to power the igniter, then the ignition process can be controlled, but the device complexity, mass, and volume increase
Solution Approach 1:
The patent combines multiple power sources (heater power source and igniter power source) into a single common power source. The heater and igniter share the same power supply, eliminating the need for separate power sources and reducing overall system complexity while maintaining reliable ignition functionality.
Solution Approach 2:
The common power source serves multiple functions: it powers both the heater during the heating phase and the igniter during the ignition phase. This multi-functional approach replaces the need for dedicated power sources for each component, reducing device complexity and mass.
2Reliability
If multiple power sources and electronic control sensors are used to power the igniter, then the ignition process can be controlled, but the mass and volume of the thruster increase
Solution Approach 1:
The patent combines multiple power sources (heater power source and igniter power source) into a single common power source. The heater and igniter share the same power supply, eliminating the need for separate power sources and reducing overall system complexity while maintaining reliable ignition functionality.
Solution Approach 2:
The patent removes electronic control sensors from the power supply system. Instead of using complex electronic sensing and control mechanisms, the system relies on passive thermal and electrical effects to automatically manage the ignition process, thereby reducing mass and volume.
3Device complexity
If a common power source is used for heater and igniter, then the power supply is simplified, but the voltage must be sufficient for both functions
Solution Approach 1:
The system dynamically transitions between different operational phases: initially the heater is activated to warm the cathode, then the igniter is activated to establish the discharge. The common power source adapts to different voltage requirements at different stages through this dynamic phase transition approach.
Solution Approach 2:
The system changes operational parameters (which component is active) based on the heating phase status. During the heating phase, the heater receives power; after sufficient heating is achieved, the igniter receives power instead. This parameter change allows a single power source to satisfy different voltage requirements at different times.
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 enhances the reliability of ignition, reduces the number of power sources, and decreases the overall mass and volume of the thruster, making it more economical and efficient.
Implementation Method 1
The passive electrical circuit comprises a capacitor C connected to the cathode reference point CRP, directly or indirectly through a resistor Ra. The capacitor C is configured to charge up to a voltage close to the voltage of the anode V, and then to discharge, forming a pulse.
Implementation Method 2
A second resistor Rb is connected in series with a diode D and the capacitor C
Implementation Method 3
The passive electrical circuit comprises a first resistor Ra, directly connected to the first power source, connected in series with a diode D and a capacitor C
Implementation Method 4
a second power source 11 intended to power a heating device 53 to heat the cathode 51 and allow it to emit electrons
Implementation Method 5
a magnetic circuit, and a cathode heating device, are well known to those skilled in the art
Data Source
Figure 1~2
Figure 3a~4
AI summary
The invention relates to an electric power supply system (1) for a Hall effect electric thruster, said Hall effect electric thruster comprising an anode (50), a cathode (51), a heating device (53) for the cathode and an igniter (52). The electric power supply system comprises: - a first power supply source (10) which is intended to supply the anode, - a second power supply source (11) which is intended to supply the heating device (53), - a power supply unit (13) which is intended to electrically supply the igniter (52) and comprising: - a third power supply source, - a passive electric circuit (131), which is supplied by said third power supply source and which is configured to generate a voltage in the form of at least one pulse.