Spacecraft Propellant Tank Segmented Holding Container
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Solution Overview
Problem
In space environments, radiant heat causes liquid phase propellants like liquid hydrogen or liquid oxygen in spacecraft tanks to evaporate, reducing the usable propellant and complicating mission execution as the evaporation rate increases with longer travel times.
Innovation Solution
A propellant tank design featuring a tank body with a holding container separated by a gap from the inner wall, using a mesh material like wire mesh or PTFE net to minimize contact and evaporation, and a gas reservoir for pressurization to discharge propellant efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If liquid phase propellant is accumulated in a conventional tank in space, then the propellant can be stored for use, but the propellant evaporates due to radiant heat from the sun
Solution Approach 1:
The tank is divided into an inner holding container and an outer tank body, creating a segmented structure. The holding container is suspended inside the tank body with gaps between them, separating the propellant storage space from the heat-prone inner wall surface. This segmentation reduces direct contact between the propellant and heated surfaces, thereby suppressing evaporation while maintaining propellant quantity.
2Device complexity
If the propellant is held in contact with the inner wall for structural simplicity, then the tank structure is simple, but the propellant evaporates when contacting the inner wall
Solution Approach 1:
The holding container acts as an intermediary structure between the propellant and the tank body. It provides a suspended storage space that mediates the interaction between propellant and heated surfaces. The container with gaps serves as a mediator that prevents direct contact while allowing the system to remain functional, reducing propellant loss without excessive structural complexity.
3Reliability
If a holding container with gaps is introduced to suppress evaporation, then propellant evaporation is suppressed, but the device complexity increases
Solution Approach 1:
The holding container is designed as a flexible or thin-walled structure that can be suspended within the tank body. This approach provides the necessary gap structure for evaporation suppression while minimizing material usage and structural complexity. The flexible shell design allows for easier manufacturing and assembly compared to rigid structures, balancing reliability improvement with acceptable device complexity.
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 design effectively suppresses propellant evaporation, ensuring a stable liquid phase supply and efficient use, even in microgravity or zero-gravity conditions, and allows for favorable propellant discharge to the engine.
Implementation Method 1
liquid phase propellant such as liquid hydrogen or liquid oxygen accumulated in the tank evaporates when coming in contact with an inner wall of the tank
Implementation Method 2
the holding container is configured by using a material on which surface tension of the propellant in a liquid state stage can act
Implementation Method 3
The propellant tank can discharge propellant accumulated therein toward an engine by pressurizing an inside thereof by operating gas
Data Source
AI summary
To provide a propellant tank such as a fuel tank and an oxidant tank for a spacecraft, the propellant tank discharging propellant such as liquid hydrogen and liquid oxygen accumulated therein toward a rocket engine by pressurizing an inside thereof by operating gas. The propellant tank includes a tank body that accumulates therein the propellant in a liquid state, and a holding container that is provided inside the tank body and disposed with a predetermined gap from an inner wall of the tank body, so that the propellant in a liquid state can be held therein, when the inside of the tank body is in a microgravity state or a zero-gravity state.