Spacecraft Cryogenic Tank Gas Extraction Device
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Solution Overview
Problem
Existing spacecraft fuel tanks face challenges in reliably separating cryogenic and non-cryogenic liquids from gases under varying acceleration conditions, leading to inefficient thrust regulation and potential liquid fuel loss during gas venting, which is energy-intensive or requires additional costly propulsion systems.
Innovation Solution
A tank arrangement with a gas supply and extraction device using baffles, capillary plates, and screens that leverage surface tension to passively separate gases from liquids, eliminating the need for active components and controllers, ensuring reliable gas extraction without residual liquids across different flight phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If heating is used to vaporize liquid fuel for gas extraction, then complete gas separation is achieved, but energy consumption increases significantly
Solution Approach 1:
The patent replaces the thermal field (heating system) with a mechanical field (centrifugal separation system). By using centrifugal force generated during spacecraft acceleration or rotation, the system mechanically separates liquid fuel from gas without requiring heating, thus eliminating the high energy consumption associated with vaporization while maintaining reliable separation.
Solution Approach 2:
The patent changes the separation parameter from temperature-based (thermal vaporization) to acceleration-based (centrifugal separation). By utilizing the spacecraft's acceleration or rotation to generate centrifugal force, the system achieves phase separation through parameter change rather than heating, resolving the contradiction between separation reliability and energy consumption.
2Reliability
If additional propulsion systems are used to accelerate spacecraft for gas-liquid separation, then separation is achieved, but system complexity and cost increase
Solution Approach 1:
The patent makes the spacecraft's propulsion system serve multiple functions: both main thrust generation and gas-liquid separation during venting operations. By utilizing the existing propulsion system's acceleration capability for dual purposes, the system achieves reliable separation without requiring additional dedicated propulsion systems, thereby reducing overall system complexity and cost.
Solution Approach 2:
The system uses the spacecraft's own propulsion system to provide the acceleration needed for gas-liquid separation during venting operations. This self-service approach eliminates the need for separate separation systems, as the existing propulsion infrastructure serves the additional function of phase separation through its acceleration capability.
3Duration of action of stationary object
If gas extraction is performed during long-duration orbital operations, then tank pressure relief is achieved, but liquid fuel loss occurs due to incomplete separation
Solution Approach 1:
The patent replaces thermal vaporization with mechanical centrifugal separation to prevent liquid fuel loss during long-duration orbital operations. By using centrifugal force to completely separate liquid from gas phases during pressure relief operations, the system ensures that only gas is vented while liquid fuel is retained in the tank, eliminating substance loss while maintaining operational duration.
4Adaptability or versatility
If varying gas-liquid mixing ratios are ejected, then thrust regulation is achieved, but thrust profile becomes non-constant requiring complex correction
Solution Approach 1:
The patent uses mechanical centrifugal separation to achieve complete and consistent gas-liquid phase separation, ensuring that only gas is ejected during venting operations. This eliminates the varying mixing ratios that cause non-constant thrust profiles, providing stable and predictable thrust while maintaining the flexibility to regulate thrust through controlled gas ejection timing and duration.
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 provides a simpler, more robust, and cost-effective gas separation system that ensures liquid-free gas extraction and supply, maintaining tank pressure while reducing the amount of inert driving gas required, thus enhancing spacecraft operation efficiency and reducing weight and complexity.
Implementation Method 1
an extraction device that uses surface tension to separate the driving gas from the liquid
Implementation Method 2
the warming of the liquid, e.g. the liquid fuel, over time generally leads to a pressure increase in the tank due to the boiling or vaporizing effect of the cryogenic liquid becoming a gas
Data Source
AI summary
A tank arrangement includes a tank for storing a liquid such as fuel or oxidizer for operation of a spacecraft and a pressurized driving gas for conveying the liquid out of the tank, and a gas supply and extraction device. The device includes a housing shell and plural outwardly expanding passage bodies providing openings that communicate the interior space of the tank to the inner reservoir space of the device. A baffle plate shields the outer opening of each passage body. Deflector plates are arranged in each passage body. Capillary plates extend longitudinally along the inner wall of the housing shell. By a capillary effect, the plates separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in a reservoir of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft.