Flight Vehicle Fluid Loop for Exterior Temperature Equalization
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Solution Overview
Problem
Flight vehicles traveling at Mach 3 experience significant temperature differentials across their exterior surfaces, leading to thermal distortion and increased fuel heat sink demand, which can compromise structural integrity and efficiency.
Innovation Solution
A system and method utilizing a fluid loop to transfer heat between exterior panels of a flight vehicle, using a working fluid to equalize temperatures and reduce temperature differentials, potentially maintaining the fluid in a supercritical state to enhance heat transfer efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If flight vehicles travel at Mach 3 speeds, then aerodynamic heating occurs causing exterior surfaces to reach high temperatures, but temperature differentials between different locations cause thermal distortion and increased fuel heat sink demand
Solution Approach 1:
A fluid loop system acts as an intermediary thermal management system between exterior panels experiencing different temperatures. The working fluid circulates through the fluid loop, absorbing heat from hotter panels and transporting it to cooler panels, thereby mediating the temperature differential caused by aerodynamic heating at Mach 3 speeds
Solution Approach 2:
The patent employs a hydraulic/fluid-based thermal management system where a working fluid circulates through a closed-loop piping system integrated with exterior panels. This pneumatic/hydraulic system efficiently transports thermal energy from high-temperature regions to low-temperature regions, resolving the temperature differential problem while maintaining high-speed flight capability
2Stability of the object's composition
If materials suitable for high temperatures are used throughout the flight vehicle, then thermal distortion is reduced, but device complexity and weight increase
Solution Approach 1:
The fluid loop system enables local thermal management, allowing different regions of the flight vehicle to have different thermal characteristics. Cooler regions can use lighter, lower-temperature materials while hotter regions are actively cooled by the fluid loop, eliminating the need to use high-temperature materials throughout the entire structure
Solution Approach 2:
The system dynamically changes the thermal parameters of exterior panels by actively transporting heat via the working fluid. This allows the thermal state of panels to be adjusted in real-time, enabling the use of materials optimized for lower temperatures while maintaining thermal stability through active thermal management
3Strength
If high-temperature materials are used to withstand aerodynamic heating, then structural integrity is maintained, but fuel heat sink demand increases
Solution Approach 1:
The system converts the harmful waste heat from hot exterior panels into a beneficial resource by transporting it to cooler panels that need heating. This heat recovery and redistribution approach reduces the overall thermal load on the structure, decreasing the fuel heat sink demand while maintaining structural integrity
Solution Approach 2:
The fluid loop system recovers thermal energy that would otherwise be discarded as waste heat from high-temperature exterior panels. By capturing and redistributing this thermal energy to cooler regions, the system reduces total heat sink requirements and improves overall thermal efficiency
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 system effectively reduces thermal distortion and structural loads by equalizing temperatures across the exterior panels, allowing for the use of materials with lower temperature characteristics and improving aerodynamic performance.
Implementation Method 1
heat is transferred from the first exterior panel to the working fluid to decrease the first initial temperature of the first exterior panel to a first altered temperature
Implementation Method 2
The heated working fluid is circulated from the first exterior panel and used to heat the second exterior panel
Implementation Method 3
A flight vehicle traveling through the atmosphere at a flight speed of at least Mach 3 may experience aerodynamic heating of an exterior surface of the flight vehicle
Data Source
AI summary
Method and system for reducing a temperature differential across a flight vehicle. The system includes an exterior of the flight vehicle. The exterior of the flight vehicle includes a first exterior panel being at a first initial temperature and a second exterior panel being at a second initial temperature to define an initial temperature differential. A fluid loop, containing a working fluid, is coupled to the first exterior panel and the second exterior panel such that heat is transferred from the first exterior panel to the working fluid to decrease the first initial temperature of the first exterior panel to a first altered temperature, and to heat the working fluid. The heated working fluid is circulated from the first exterior panel and used to heat the second exterior panel to a second altered temperature greater than the second initial temperature.