Rocket Stage Propellant Swap via Valve and Sensor Interchange
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Solution Overview
Problem
Existing rocket stages optimized for specific propellant loads face limitations in performance and cost, as they are designed to minimize gross liftoff weight and maximize engine exhaust velocity, but these designs do not account for potential improvements through re-propellantation or fuel swaps.
Innovation Solution
The proposed solution involves swapping valves, sensors, and fittings between hydrogen and oxygen tanks in an existing rocket stage, converting the hydrogen tank to store liquid oxygen and the oxygen tank to store liquid hydrogen or hydrocarbon fuels, while maintaining the same engine and sensors, thereby enabling the use of denser warm cryogenic fuels like propane, methane, or butane.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If existing rocket stages are optimized for specific propellant loads to minimize gross liftoff weight and maximize engine exhaust velocity, then performance is improved, but adaptability to different fuel types is lost
Solution Approach 1:
The patent applies parameter changes by swapping propellants between tanks (liquid hydrogen with liquid oxygen, or vice versa, or using hydrocarbon fuels) and changing the corresponding sensors and valves to match the new propellant combinations, enabling the same rocket stage hardware to operate with different fuel types without major redesign
Solution Approach 2:
The patent achieves universality by designing the rocket stage system to be multi-functional through propellant swapping capability, where the same tanks, engines, and structure can support multiple propellant combinations (liquid hydrogen/liquid oxygen, hydrocarbon/oxidizer, etc.) by simply changing valves and sensors rather than requiring dedicated hardware for each fuel type
2Speed
If denser warm cryogenic fuels like propane, methane, or butane are used instead of liquid hydrogen, then delta V and orbital duration are improved, but stage weight increases
Solution Approach 1:
The patent applies parameter changes by switching from liquid hydrogen (low density, high specific impulse) to denser warm cryogenic fuels like propane, methane, or butane. This changes the density parameter of the propellant, allowing more mass to be stored in the same tank volume, which increases delta V and orbital duration despite the heavier stage weight
3Ease of manufacture
If existing rocket stage infrastructure is repurposed for different propellants, then development costs are reduced, but sensor and valve compatibility challenges arise
Solution Approach 1:
The patent applies parameter changes by systematically swapping not only propellants but also the corresponding sensors and valves to match the new propellant combinations. This ensures chemical compatibility and proper sensing functionality while maintaining the same tank and engine hardware, thereby reducing development costs while maintaining reliability
Solution Approach 2:
The patent uses valves and sensors as intermediaries that can be swapped to accommodate different propellant types. These components act as mediators between the fixed tank/engine infrastructure and the variable propellant requirements, enabling cost-effective repurposing while ensuring proper functionality and compatibility
Data Source
AI summary
The present invention relates to an improved rocket stage and a method of improving an existing rocket stage. In an embodiment, the improved rocket stage is where one can take existing rocket stages and re-propellant them. In another embodiment, the present invention is a method of improving an existing rocket stage.