Aircraft Fairing Air Inlet Integrated Into Stiffener Structure
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing fairings in aircrafts face limitations in positioning air inlets due to structural elements like stiffeners, which obstruct airflow and reduce cooling efficiency while maintaining structural integrity.
Innovation Solution
Integrating an air inlet device, such as a NACA duct, into the stiffener element or stringer of the fairing, allowing airflow through without cutting the stiffener, thereby maintaining structural strength and optimizing cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If an air inlet device is positioned in the fairing wall, then cooling efficiency is improved, but structural strength is reduced due to the presence of stiffeners
Solution Approach 1:
The air inlet device is integrated into the stiffener element, merging two previously separate components (air inlet device and stiffener) into a single unified structure. This allows the stiffener to simultaneously serve its structural function and provide a pathway for airflow, resolving the contradiction between maintaining structural strength and enabling effective cooling.
Solution Approach 2:
The air inlet device is nested within the stiffener element, with the inlet opening positioned in the stiffener and the duct extending through or into it. This nesting arrangement allows the air inlet functionality to be embedded within the structural stiffener, maintaining overall structural integrity while enabling airflow passage.
2Temperature
If the air inlet is positioned forward in the fairing, then cooling efficiency is improved, but the fairing split location prevents placement
Solution Approach 1:
By merging the air inlet device with the stiffener element, the invention overcomes the limitation imposed by the fairing split. The integrated design allows the air inlet to be positioned at optimal locations regardless of fairing segmentation, as the stiffener provides a continuous structural and functional pathway.
3Strength
If the air inlet is positioned aft in the fairing, then structural elements are avoided, but cooling efficiency is reduced
Solution Approach 1:
The integration of the air inlet device into the stiffener element eliminates the need to choose between avoiding structural elements and achieving optimal cooling positions. The stiffener serves dual purposes: maintaining structural integrity and providing an optimized airflow pathway to cooling components.
4Temperature
If a separate air inlet device is added to the fairing, then cooling functionality is improved, but device complexity increases
Solution Approach 1:
The invention merges the air inlet device with the existing stiffener element, reducing the total number of separate components. Instead of adding a standalone air inlet device to the fairing wall, the functionality is integrated into the already-present stiffener, simplifying the overall structure.
Solution Approach 2:
The stiffener element is given multiple functions: it maintains structural integrity of the fairing and simultaneously serves as the housing and pathway for the air inlet device. This multi-functionality reduces component count and simplifies the overall system design.
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
Enhances airflow efficiency for cooling components within the fairing without compromising structural integrity, reducing drag and weight, and allowing flexible design placement.
Implementation Method 1
an inlet opening to allow a part of the free air flow outside the fairing to pass through the wall element and to enter the interior of the fairing
Implementation Method 2
at least one stiffener element attached to the inner surface of the wall element, to keep the fairing in shape under dynamic pressure loads
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A fairing (10), in particular for an aircraft, comprises a wall element (12) comprising an inner surface (16) and an outer surface (14), wherein the outer surface (14) is exposed to a free air flow (F) outside the fairing (10), and at least one stiffener element (18) attached to the inner surface (16) of the wall element (12), to keep the fairing in shape under dynamic pressure loads. The fairing (10) comprises at least one air inlet device (22) comprising an inlet opening (26) to allow a part of the free air flow (F) outside the fairing (10) to pass through the wall element (12) and to enter the interior of the fairing (10). The air inlet device (22) is at least partially integrated into the stiffener element (18), and the inlet opening (26) of the air inlet device (22) is formed in the stiffener element (18) and extends into or through the stiffener element (18). The air inlet device (22) and the stiffener element (18) may be integrally formed as one single part, preferably by 3D printing.