Aircraft Nacelle Load Support Segmentation for Aerodynamic Stability
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Solution Overview
Problem
The existing propulsion assembly for aircraft causes disturbance in air flow due to the deformation of the aerodynamic upper surface of the load support, which offsets the aerodynamic surface of the nacelle, leading to undesirable air flow disturbances.
Innovation Solution
The propulsion assembly separates the load support into two parts, with a structural part fastened to the pylon and an aerodynamic part capping the structural part, using a complex system of articulated rods to reduce the movement of the aerodynamic surface, thereby minimizing the disturbance caused by the load support's movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the load support is fastened to the pylon and fan casing by rods, then the load support can follow engine movements, but the aerodynamic upper surface offsets and deforms the aerodynamic surface of the nacelle, leading to air flow disturbance
Solution Approach 1:
The aerodynamic part is divided into a front part and a rear part that can move independently. The front part is fastened to the structural part of the load support, while the rear part is fastened to the pylon, allowing differential movement to maintain aerodynamic surface alignment
Solution Approach 2:
The aerodynamic part is made dynamic by allowing its front and rear sections to move relative to each other through articulated rods, enabling the aerodynamic surface to adapt to engine movements while maintaining proper alignment with the nacelle
2Object-affected harmful factors
If the aerodynamic part is separated into front and rear parts fastened differently, then the movements of the aerodynamic part are reduced, but the device complexity increases
Solution Approach 1:
The aerodynamic part is segmented into front and rear portions with distinct fastening arrangements, allowing independent movement control to minimize aerodynamic surface offset while managing complexity through functional division
Data Source
AI summary
A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.