Aircraft Nacelle Duct Connection with Internal Access
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft nacelle connections require removable covers for accessing connecting elements, increasing on-board mass and complicating the assembly process due to the need for external access.
Innovation Solution
A single series of connecting elements is used to connect the air inlet and engine ducts, made of composite material, allowing internal access and elimination of external cowls, with recesses in acoustic panels to house connecting element heads and O-rings for sealing, and deformable connecting blades for stress management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If removable covers are provided on the outer wall to access connecting elements, then the connecting elements can be accessed from outside the nacelle, but the on-board mass increases and the structure becomes more complex
Solution Approach 1:
The patent inverts the conventional approach by enabling access to connecting elements from inside the nacelle rather than outside. The connecting elements are designed with internal access features, eliminating the need for external removable covers. This inversion resolves the contradiction by removing the covers (reducing mass) while maintaining accessibility through the alternative internal route.
2Strength
If multiple series of connecting elements are used to link ducts and panels, then structural integrity is improved, but the number of connecting elements increases and assembly complexity increases
Solution Approach 1:
The patent merges multiple separate connection systems into a single integrated series of connecting elements. Instead of having separate connecting elements for linking ducts to panels and panels to each other, the invention uses one unified series of connecting elements that performs all these functions. This merging maintains structural integrity while reducing the total number of connecting elements and simplifying assembly.
3Weight of moving object
If composite materials are used for acoustic panels and ducts, then weight is reduced, but the number of connecting elements increases when integrated with metal flanges
Solution Approach 1:
The patent employs composite materials for acoustic panels and ducts to achieve weight reduction. The composite structure is designed to integrate directly with the connecting elements, eliminating the need for separate metal flanges. This direct integration maintains the weight benefits of composite materials while avoiding the increase in connecting elements that would result from adding metal flange interfaces.
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 design reduces on-board mass, simplifies assembly by allowing internal access, and enhances structural integrity through efficient stress distribution and sealing.
Implementation Method 1
an acoustically resistive layer 24
Implementation Method 2
at least one alveolar layer 26
Data Source
Figure 1~2
Figure 3A~5
Figure 6~8
AI summary
The object of the invention is an aircraft nacelle which includes a duct attached to an air inlet (50) and a duct attached to a motor (56), a linkage (76) between the duct attached to the air inlet (50) and the duct attached to the motor (56) which includes: - a sleeve (78) which receives one end of a first duct (52) and is attached to a second duct (54), - connecting elements (80) which connect the sleeve (78) and the first duct (52) and which are distributed over the entire circumference of the nacelle, each connecting element (80) having a threaded rod oriented in a radial direction and being configured to allow its tightening from inside the first duct (52).