Aircraft Tail Cooling System with Integrated Skin Cooler
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Solution Overview
Problem
Current aircraft cooling systems increase air resistance and fuel consumption due to air inlet and outlet openings in the outer skin, and have limited cooling power and high weight, making them inefficient for handling thermal loads from heat-generating devices like fuel cells.
Innovation Solution
An aircraft tail region cooling system with a detachable cooler integrated into the outer skin, featuring coolant channels and a fan system, which operates efficiently by utilizing ambient air flow and pressure differences to minimize weight and maximize cooling power, and includes adjustable lamellae for controlling air flow to optimize fuel efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If air inlet and outlet openings are formed in the aircraft outer skin for cooling, then cooling function is provided, but air resistance increases and fuel consumption increases
Solution Approach 1:
The cooler is merged with the aircraft outer skin, forming an integrated structure where the cooler becomes part of the outer skin itself. This eliminates the need for separate air inlet and outlet openings in the outer skin, as the cooler's own structure provides the cooling function while maintaining aerodynamic integrity.
Solution Approach 2:
The cooler serves multiple functions: it acts as both a cooling device and a structural component of the aircraft outer skin. The cooler's housing forms part of the aerodynamic surface, simultaneously providing thermal management and maintaining structural integrity while reducing air resistance compared to traditional separate opening designs.
2Temperature
If traditional aircraft cooling systems with ram air inlets are used, then cooling is provided, but cooling power is limited and weight is high
Solution Approach 1:
The system dynamically adapts its cooling mode based on flight conditions. During flight, it utilizes free stream air flow through the cooler. During ground operation, it activates the fan system to force air through the cooler, thereby maximizing cooling power in both operational states without being limited by ram air inlet constraints.
Solution Approach 2:
During flight operations, the cooling system utilizes the aircraft's own motion through the air to provide cooling, requiring no additional power input for air intake. The free stream air flow automatically passes through the cooler, eliminating the need for powered ram air inlets and reducing overall system weight while maintaining high cooling power.
3Weight of stationary object
If the cooler is integrated into the aircraft outer skin, then weight is reduced and cooling power is increased, but manufacturing complexity increases
Solution Approach 1:
The cooler is designed as a detachable module that can be separately manufactured and then installed in the aircraft outer skin. This segmentation allows the cooler to be produced independently using optimized processes, reducing overall manufacturing complexity while achieving the weight and performance benefits of integration.
Solution Approach 2:
The coolant channels are integrated within the cooler's housing structure, with the cooling functionality nested inside the outer skin component. This nested design allows the cooler to function as both a structural element and a thermal management device, reducing total weight while managing the manufacturing complexity through modular construction.
4Power
If fan system is added to convey ambient air through coolant channels, then cooling power is increased, but device complexity increases
Solution Approach 1:
During flight, the cooling system is self-sufficient, using the aircraft's forward motion to drive air through the cooler without requiring fan activation. The fan system serves only as a supplemental component for ground operations, significantly reducing overall system complexity compared to systems that require continuous powered operation.
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 provides high cooling power with low pressure losses and weight savings, allowing efficient thermal load management from heat-generating devices while reducing air resistance and fuel consumption.
Implementation Method 1
ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region in conveying operation of the fan system is discharged back into the aircraft environment
Implementation Method 2
a cooler (14) which forms a section of an outer skin (16) of the aircraft tail region (10) and comprises coolant channels (20) allowing a flow of ambient air therethrough
Data Source
AI summary
An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment.