Thermal management system
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current thermal management systems for electric aircraft are burdensome due to mass requirements for cooling high-power electric motors and electronics, and traditional cooling methods are inadequate for future cryogenic systems with higher voltages, posing spark ignition hazards and inefficiencies.
Innovation Solution
A thermo-acoustic-based thermal management system that utilizes waste heat from turbo-generators to create acoustic waves for power generation and component cooling, using hollow tubes to propagate energy and heat efficiently throughout the aircraft, eliminating the need for heavy cooling fluids and complex plumbing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional convective cooling with jet fuel is used, then cooling safety is maintained at lower voltages, but the system becomes inadequate for high-voltage cryogenic systems and increases mass
Solution Approach 1:
The patent changes the cooling parameter from ambient temperature jet fuel to cryogenic temperatures (near absolute zero), enabling flight-weight electric motors and optimized system efficiency while using acoustic wave technology to manage the thermal challenges of cryogenic cooling
Solution Approach 2:
The patent replaces traditional mechanical cooling systems (pumps, plumbing, heat exchangers) with a thermo-acoustic system that uses acoustic waves to transfer heat, eliminating the need for heavy mechanical components and complex cryogenic plumbing
2Power
If cryogenic temperatures are used for optimal motor performance, then power and efficiency are improved, but thermal management system mass increases
Solution Approach 1:
The patent replaces heavy mechanical cooling systems with a thermo-acoustic system that uses sound waves to transfer heat energy, dramatically reducing the mass of the thermal management system while maintaining cryogenic operating temperatures for optimal motor efficiency
Solution Approach 2:
The patent distributes multiple small acoustic sources throughout the aircraft rather than using a single large cooling system, with each acoustic source managing heat in its local region, thereby reducing overall system mass while maintaining effective cryogenic cooling
3Power
If higher bus voltage (4500V) is used to optimize system mass and efficiency, then power system efficiency is improved, but spark ignition hazard increases
Solution Approach 1:
The patent uses cryogenic temperatures to create an inert environment where alternative fuels like liquid methane or hydrogen cannot ignite from sparks, enabling the use of high-voltage (4500V) power systems for optimized mass and efficiency while eliminating the spark ignition hazard through the inerting effect of cryogenic temperatures
4Temperature
If liquid nitrogen and heat pump systems are used for cryogenic cooling, then cooling capability is achieved, but system complexity and mass increase
Solution Approach 1:
The patent replaces complex mechanical heat pump systems with a thermo-acoustic system that uses acoustic waves to transfer heat, eliminating the need for coolant pumps, vacuum jacketed plumbing, and large heat exchangers, thereby achieving cryogenic cooling with dramatically reduced system complexity and mass
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 system achieves lightweight, fuel-efficient, and safe thermal management by converting waste heat into usable energy for cooling and power, reducing mass, drag, and maintenance while avoiding spark ignition risks, suitable for both ambient and cryogenic systems.
Implementation Method 1
a plurality of thermo-acoustic engines configured to absorb waste heat from a plurality of aircraft engines... converting the engine waste heat into mechanical energy
Implementation Method 2
a plurality of first hollow tubes disposed in the aircraft configured to propagate mechanical energy to locations throughout the aircraft
Implementation Method 3
a plurality of heat pumps configured to absorb electrical component waste heat from electrical components of the aircraft... converting the mechanical energy into usable electric energy, powering aircraft electrical components including the plurality of heat pumps
Implementation Method 4
a plurality of heat pipe hollow tubes configured to transfer the electrical component waste heat to the aircraft engines
Data Source
AI summary
A thermal management system for an aircraft is provided that includes thermo-acoustic engines that remove and capture waste heat from the aircraft engines, heat pumps powered by the acoustic waves generated from the waste heat that remove and capture electrical component waste heat from electrical components in the aircraft, and hollow tubes disposed in the aircraft configured to propagate mechanical energy to locations throughout the aircraft and to transfer the electrical component waste heat back to the aircraft engines to reduce overall aircraft mass and improve propulsive efficiency.