Liquid Methane Pressurization Cylinder for Rocket Propellant Tanks
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Solution Overview
Problem
The existing cryogenic high-pressure gaseous pressurization technology for rockets propelled by liquid oxygen and methane is costly and poses safety hazards due to the risk of combustion and explosion when using conventional materials in liquid oxygen environments.
Innovation Solution
A pressurization device with a pressurized gas cylinder in the liquid methane tank, featuring a heat exchange structure, gas flow regulation, and an energy dissipator, which allows safe and efficient pressurization by using titanium alloy cylinders in the liquid methane tank, reducing material costs and enhancing payload capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If ordinary titanium alloy or non-metallic materials are used in the pressurized gas cylinder placed in liquid oxygen tank, then the cylinder can be manufactured with lower cost or easier process, but combustion reaction occurs with liquid oxygen leading to safety hazards
Solution Approach 1:
The patent introduces liquid methane as an intermediary medium to separate the pressurized gas cylinder from direct contact with liquid oxygen. The cylinder is placed in the liquid methane tank instead of directly in the liquid oxygen tank, using liquid methane as a protective barrier that prevents combustion reactions while allowing the cylinder to function normally for pressurization
2Reliability
If flame-retardant titanium alloy materials are used to ensure safety in liquid oxygen environment, then safety hazards are reduced, but material cost increases ten times or more
Solution Approach 1:
By introducing liquid methane as an intermediary medium, the patent allows the use of ordinary titanium alloy or non-metallic materials in the pressurized gas cylinder without direct exposure to liquid oxygen. This eliminates the need for expensive flame-retardant materials while maintaining safety through the protective barrier of liquid methane
3Reliability
If high-temperature alloys are used to improve compatibility with liquid oxygen, then safety is improved, but specific gravity increases leading to higher weight
Solution Approach 1:
The patent uses liquid methane as an intermediary medium that allows lightweight materials (ordinary titanium alloy or non-metallic materials) to be used in the pressurized gas cylinder. This avoids the need for heavy high-temperature alloys while maintaining safety through the protective barrier, thus reducing the overall weight of the pressurization system
4Device complexity
If the pressurized gas cylinder is placed directly in the liquid oxygen tank, then the pressurization system is simplified, but combustion reaction occurs leading to safety hazards
Solution Approach 1:
The patent implements a nested structure where the pressurized gas cylinder is placed inside the liquid methane tank, which itself is inside or integrated with the liquid oxygen tank system. This nested arrangement allows the cylinder to be protected by the liquid methane barrier while maintaining a compact and relatively simple overall pressurization system structure
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 solution reduces safety hazards and costs by using titanium alloy cylinders in the liquid methane tank, improves heat exchange efficiency, and increases payload capacity by optimizing gas storage density and pressurization efficiency during flight.
Implementation Method 1
a pressurized gas enters the propellant tank, expands and occupies the space of a discharged propellant, and generates a working pressure on the liquid propellant
Implementation Method 2
the pressurized gas cylinder being communicated with the pressurized gas inlet through a pipeline, featuring a heat exchange structure
Data Source
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AI summary
The present invention relates to the field of liquid rocket technology, and in particular, to a pressurization device for a rocket propelled by liquid oxygen and methane and a rocket propelled by liquid oxygen and methane. The pressurization device for a rocket propelled by liquid oxygen and methane comprises: a liquid oxygen tank provided with a pressurized gas inlet; and a liquid methane tank provided with a pressurized gas cylinder therein, the pressurized gas cylinder being communicated with the pressurized gas inlet through a pipeline. The present invention provides a pressurization device for a rocket propelled by liquid oxygen and methane and a rocket propelled by liquid oxygen and methane with a low cost while ensuring safety.