Space Gas Transfer via Thermal Pressure Cycling
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Solution Overview
Problem
Existing space-based gas resupply systems for spacecraft are inefficient due to the need for equalizing tank pressures and require redundant and maintenance-intensive electro-mechanical equipment like pumps and compressors, limiting the amount of gas transferred and increasing launch costs.
Innovation Solution
A space-based gas supply system that uses a transfer tank with a heating system to increase gas pressure, allowing efficient transfer to a receiving tank without rotating mechanical equipment, and optionally incorporates a cooling system or variable volume tank with a working gas system to enhance efficiency, reducing the need for maintenance and redundancy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If pressure equalization method is used to transfer gas from supply tank to receiving tank, then gas transfer can be achieved without mechanical equipment, but only a limited amount of gas can be transferred until pressures equalize, leaving substantial gas remaining in the supply tank
Solution Approach 1:
The patent changes the temperature parameter of the transfer tank to control gas pressure. By heating the transfer tank, gas pressure increases enabling transfer to the receiving tank. By cooling the transfer tank, gas pressure decreases enabling refill from the supply tank. This temperature-based parameter control allows multiple transfer cycles without mechanical equipment, significantly increasing the total amount of gas transferred while minimizing waste.
2Quantity of substance
If electro-mechanical pumps or compressors are used to increase gas transfer amount, then more gas can be transferred from supply tank to receiving tank, but the system requires high degree of redundancy and maintenance, increasing weight and launch cost
Solution Approach 1:
The patent replaces electro-mechanical pumps and compressors with a thermal-based system. Instead of using mechanical compression to increase gas pressure, the system uses heating elements to thermally expand the gas in the transfer tank, creating the pressure differential needed for transfer. This substitution eliminates complex mechanical components, reducing redundancy requirements, maintenance needs, system weight, and launch costs while achieving the same gas transfer functionality.
3Productivity
If electro-mechanical pumps or compressors are used for gas transfer, then gas transfer efficiency is improved, but system weight increases due to required redundancy and maintenance components
Solution Approach 1:
The patent substitutes mechanical compression systems with thermal expansion systems. Heating elements in the transfer tank thermally expand the gas to create pressure for efficient transfer, eliminating the need for heavy electro-mechanical pumps and compressors. This reduces system weight significantly while maintaining or improving gas transfer efficiency through controlled thermal cycles that enable multiple transfer operations.
4Device complexity
If simple pressure equalization is used for gas transfer, then system complexity is reduced, but the amount of gas that can be transferred is limited and resupply efficiency decreases
Solution Approach 1:
The patent introduces temperature as a controllable parameter to enhance the simple pressure equalization concept. By cycling the temperature of the transfer tank between heating and cooling, the system creates multiple pressure differential cycles. Each heating cycle enables gas transfer to the receiving tank, and each cooling cycle enables refill from the supply tank. This thermal cycling approach maintains simple system architecture without mechanical equipment while dramatically improving resupply efficiency and the total amount of gas transferred.
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 system enables a more efficient transfer of gas beyond simple pressure equalization, reducing maintenance requirements and launch weight by eliminating the need for rotating electro-mechanical equipment, ensuring reliable and cost-effective resupply of spacecraft in space.
Implementation Method 1
activating the heating system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is increased
Implementation Method 2
activating the cooling system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is decreased
Data Source
AI summary
A transfer system for supplying a receiving tank of a receiving spacecraft with a supply gas from a supply spacecraft. A transfer tank is disposed on the supply spacecraft and configured to retain a supply gas. A transfer line is coupled to the transfer tank, and one end thereof may be coupled to the receiving tank. A transfer valve is operatively coupled to the transfer line. A heating system is thermally coupled to the transfer tank. A control system is operatively coupled to the transfer valve and the heating system. The control system is operable to cause a transfer quantity of the supply gas to be heated, and to open the transfer valve, such that a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes the transfer quantity of the supply gas to flow to the receiving tank.