LNG Fueling Control System for Launch Vehicles
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Solution Overview
Problem
Existing methods for loading Liquefied Natural Gas (LNG) propellant into space launch vehicles rely on volumetric targets, which fail to account for variations in the composition of LNG due to temperature changes and other factors, leading to inaccuracies in weight and engine operation.
Innovation Solution
A control system that monitors the flow of LNG into the launch vehicle's tank using spectroscopic or chromographic analyzers to determine the real-time composition and density of the fuel, allowing for precise control of the fueling process based on mass targets.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If volumetric loading target is used for loading LNG propellant, then the loading process is simple, but the weight and composition accuracy deteriorate due to composition variations with temperature
Solution Approach 1:
The system transitions from volumetric measurement to mass-based measurement by continuously monitoring LNG composition and calculating mass using density corrections. The control system adjusts the loading parameter from volume to mass, accounting for temperature-induced composition changes, thereby resolving the contradiction between loading simplicity and measurement accuracy.
Solution Approach 2:
The system implements continuous feedback by monitoring LNG composition during loading, calculating real-time density corrections, and adjusting the loading process to achieve the desired mass target. This feedback loop ensures accurate weight control while maintaining operational simplicity through automated corrections.
2Device complexity
If volumetric loading is used, then the equipment complexity is low, but the engine operation reliability deteriorates due to composition variations
Solution Approach 1:
The control system continuously monitors LNG composition and provides feedback to adjust the loading process, ensuring consistent mass delivery despite temperature and composition variations. This feedback mechanism enhances engine operation reliability while keeping equipment complexity manageable through software-based corrections.
Solution Approach 2:
The system replaces complex mechanical measurement equipment with a control system that uses composition monitoring and computational density corrections to achieve accurate mass measurement. This substitution maintains reliability while avoiding the need for complex additional hardware.
3Measurement precision
If real-time composition monitoring is implemented, then the mass loading accuracy is improved, but the device complexity increases due to additional sensors and processing
Solution Approach 1:
The control system performs multiple functions: it monitors composition, calculates density corrections, determines mass, and controls the loading process. By making the control system multi-functional, the patent avoids the need for separate dedicated devices for each function, thereby improving mass loading accuracy without proportionally increasing 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
This approach ensures accurate and efficient loading of LNG, aligning with mass targets and accounting for compositional changes, thereby improving the reliability and performance of space launch vehicles.
Implementation Method 1
reading, from a spectroscopic or chromographic analyzer, at a periodic time interval, raw composition values for the fuel
Implementation Method 2
reading, from a spectroscopic or chromographic analyzer, at a periodic time interval, raw composition values for the fuel
Data Source
AI summary
Embodiments disclosed herein are directed to controlling the fueling process for a space launch vehicle based on a composition of a Liquefied (LNG) propellant being loaded onto the space launch vehicle. According to one embodiment, controlling a fueling process for a launch vehicle can comprise monitoring a flow of a fuel being loaded into a tank of the launch vehicle during the fueling process. Loading of the fuel into the tank of the launch vehicle can then be controlled based on the determined mass of the fuel and a predefined mass loading target for the fuel.