Integrated Vehicle Fluids System for Space Launch Enthalpy Recovery
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Solution Overview
Problem
Current rocket propulsion systems for space launch vehicles rely on separate hydrazine systems and helium-based pressurization, which are costly, complex, and limited in capability, leading to inefficiencies and propellant losses during long-duration missions.
Innovation Solution
The use of ullage gases from the hydrogen and oxygen tanks to power an internal combustion engine, which generates power for attitude control, propellant settling, and tank pressurization, eliminating the need for separate hydrazine and helium systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate hydrazine systems and helium-based pressurization are used, then reliability is maintained, but device complexity and cost increase
Solution Approach 1:
The patent merges the pressurization function and power generation function into a single integrated system. The internal combustion engine uses ullage gases from the propellant tanks to generate power, while the same system manages pressurization, eliminating the need for separate helium-based pressurization systems and hydrazine systems. This integration reduces overall system complexity while maintaining reliability through unified control.
Solution Approach 2:
The internal combustion engine serves multiple functions simultaneously: it generates electrical power, manages propellant tank pressurization, and utilizes waste ullage gases. This multi-functionality replaces what would traditionally require separate dedicated systems for each function, thereby reducing device complexity while preserving system reliability.
2Reliability
If separate hydrazine systems and helium-based pressurization are used, then system functions are reliable, but loss of substance increases due to propellant losses
Solution Approach 1:
Instead of discarding waste ullage gases from the propellant tanks, the system recovers and utilizes them as fuel for the internal combustion engine. This recovery process converts what would be wasted propellant into useful energy and power, thereby reducing propellant losses while maintaining system function reliability.
Solution Approach 2:
The patent converts the harmful effect of waste ullage gases (which would normally be vented and cause propellant loss) into a beneficial resource by using them as fuel for the internal combustion engine. This transforms a loss into a gain, producing power while reducing overall propellant consumption.
3Reliability
If separate pressurization systems are used, then tank pressurization is reliable, but weight increases due to mass penalty
Solution Approach 1:
The patent combines the pressurization function with the power generation function in a single integrated system. The internal combustion engine manages both power production and propellant tank pressurization, eliminating the need for separate helium-based pressurization systems. This merging reduces the total mass of the vehicle while maintaining reliable tank pressurization through unified system control.
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 approach reduces propellant losses, simplifies the vehicle systems, and enables longer mission durations by utilizing waste gases efficiently and eliminating the mass penalty of separate pressurization systems.
Implementation Method 1
The use of ullage gases from the hydrogen and oxygen tanks to power an internal combustion engine, which generates power for attitude control, propellant settling, and tank pressurization
Implementation Method 2
heat exchangers that transfer heat directly from the internal combustion engine to the propellants
Data Source
AI summary
A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.