Spacecraft Electrolyzer Using Passive Matrix for Propellant Generation
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Solution Overview
Problem
Existing spacecraft drive systems lack efficient and environmentally friendly methods for on-site generation of hydrogen and oxygen, often requiring complex components and high energy consumption, which is not suitable for sporadic or long-term operations.
Innovation Solution
A drive fabric generating device equipped with an electrolyzer using an alkaline electrolyte, featuring a matrix electrolytic cell, water reservoir, and pressure equalization valves, which periodically generates hydrogen and oxygen at elevated pressures for spacecraft propulsion, minimizing active components and energy requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional electrolyzers are used for hydrogen and oxygen production in spacecraft, then propellant can be generated, but the system requires complex active components such as sensors, control components, cooling pumps, compressors, and water pumps
Solution Approach 1:
The patent removes all active components (sensors, control components, cooling pumps, compressors, water pumps) from the electrolyzer system, retaining only the essential electrolysis cell with passive matrix electrode and alkaline electrolyte. This extraction of non-essential components directly resolves the contradiction by simplifying the system while maintaining propellant generation capability.
Solution Approach 2:
The passive matrix electrode structure automatically performs multiple functions: it provides electrocatalytic activity, self-cooling through thermal conductivity, and self-pressurization through gas generation. The system serves itself without external control, eliminating the need for active components and resolving the complexity issue.
2Reliability
If conventional electrolyzers with active components are used, then controlled propellant generation is possible, but energy consumption increases due to multiple active components
Solution Approach 1:
By removing active components that consume energy (pumps, compressors, cooling systems), the patent dramatically reduces energy consumption while maintaining reliable propellant generation through the passive matrix electrode's inherent electrocatalytic and thermal management properties.
3Productivity
If frequent propellant generation is required, then sufficient propellant supply can be ensured, but system wear and energy consumption increase
Solution Approach 1:
The passive matrix electrode structure with high thermal conductivity provides self-cooling during operation, preventing thermal degradation and extending component lifespan. This enables frequent propellant generation cycles without increasing system wear, as the structure automatically manages its own thermal load.
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
Enables simple, fast, and environmentally friendly on-site generation of hydrogen and oxygen for spacecraft drives, reducing the need for complex systems and energy consumption, while ensuring reliable and long-term gas storage for propulsion.
Implementation Method 1
an electrolyzer (14) designed for recurring production of hydrogen and oxygen and having at least one electrolysis cell (16) with at least one alkaline electrolyte. Water is split into molecular oxygen and molecular hydrogen by absorbing energy through an electric current
Implementation Method 2
at least one electrolysis cell (16) formed by a matrix cell
Data Source
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AI summary
The invention proposes a propellant generation device for a spacecraft (12), in particular for a satellite, comprising at least one electrolyzer (14) which is provided for the periodic generation of hydrogen and oxygen and has at least one electrolysis cell (16) comprising at least one alkaline electrolyte (18).