Aircraft Peltier Cooling Assembly Without Ram Air Channels
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Solution Overview
Problem
Current aircraft cooling systems rely on ram air channels and external cooling elements, which are inefficient and require complex control units, and do not effectively utilize internal thermal energy dissipation without introducing cold ambient air.
Innovation Solution
A Peltier element-based cooling assembly that dissipates thermal energy from a thermal body to the aircraft structure using a cold side, with a controllable fan and cooling device to manage air flow and improve heat transport, allowing for internal cooling without external air intake and minimizing power consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ram air channels are used for cooling, then cooling effectiveness is improved, but air resistance increases and structural efficiency decreases
Solution Approach 1:
The invention extracts the cooling function from the external ram air channel structure and relocates it to an internal Peltier element. This removes the need for complex external cooling structures that create air resistance, while maintaining effective cooling through solid-state thermoelectric cooling within the aircraft component itself.
Solution Approach 2:
The Peltier element acts as an intermediary device that converts electrical energy directly into thermal energy transfer, eliminating the need for mechanical ram air channels. This intermediary approach provides more efficient cooling with minimal structural impact and no additional air resistance.
2Temperature
If bleed air system is used for cooling, then sufficient cool air is provided, but air mass flow in power plant is reduced
Solution Approach 1:
The Peltier element provides self-contained cooling by directly converting electrical energy into thermal energy transfer at the component level. This self-service cooling mechanism eliminates the need to extract bleed air from the power plant, maintaining full air mass flow for power generation while providing independent cooling capability.
Solution Approach 2:
The invention replaces the mechanical bleed air cooling system with an electrical solid-state Peltier cooling system. This substitution eliminates the trade-off between cooling capability and power plant air mass flow, as the electrical system does not compete with the pneumatic system for air resources.
3Temperature
If liquid cooling systems are used, then cooling of aircraft components is improved, but system complexity and weight increase
Solution Approach 1:
The invention extracts the cooling function from complex liquid cooling systems with pumps, radiators, and coolant loops, and implements it through a compact Peltier element. This extraction eliminates heavy liquid cooling infrastructure while maintaining effective component cooling through direct solid-state thermoelectric cooling.
Solution Approach 2:
The invention replaces hydraulic/liquid cooling systems with an electrical solid-state system. The Peltier element provides cooling without requiring liquids, pumps, or complex fluid circulation systems, thereby significantly reducing system weight and complexity while maintaining cooling effectiveness.
4Ease of operation
If control units are added for cooling management, then cooling control is improved, but device complexity increases
Solution Approach 1:
The Peltier element provides inherent cooling control through its electrical characteristics, where cooling capacity is directly proportional to electrical current. This self-service control mechanism eliminates the need for complex control units, sensors, and feedback systems, as the cooling effect is naturally regulated by electrical power management.
Solution Approach 2:
The invention controls cooling by simply changing electrical parameters (current, voltage, power) to the Peltier element. This parameter-based control is inherently simpler than mechanical or pneumatic control systems, as it requires only basic electrical circuitry rather than complex control units, valves, or actuators.
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
Enables efficient, controllable, and internal cooling of aircraft components by leveraging the temperature difference between the aircraft environment and thermal bodies, reducing the need for ram air channels and external cooling elements, while saving weight and cost through simplified design and reduced power usage.
Implementation Method 1
The cooling assembly has a Peltier element with a hot side and a cold side. The thermal body is arranged in heat-conductive contact with the cold side of the Peltier element. The hot side of the Peltier element is adapted to dissipate thermal energy to an aircraft structure, such that the thermal body is coolable.
Data Source
AI summary
A cooling assembly for cooling a thermal body for an aircraft. The cooling assembly has a Peltier element with a hot side and a cold side. Furthermore, the cooling assembly has a thermal body. The thermal body is arranged in heat-conductive contact with the cold side of the Peltier element. The hot side of the Peltier element is adapted to dissipate thermal energy to an aircraft structure, such that the thermal body may be cooled.