Hinged Cover System for Aircraft Nacelle Maintenance Access
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Solution Overview
Problem
Current aircraft turbine engine assemblies require lengthy maintenance procedures due to the need to remove and replace multiple fastened covers to access systems between the attachment strut and engine, hindering efficient access and maintenance.
Innovation Solution
A hinged cover system is integrated into the nacelle, featuring a hinge system and locking mechanism that allows the cover to transition between closed and open positions, facilitating access to systems at the joint between the attachment strut and engine, and reducing the need for multiple cover removals.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple fastened covers are used to protect systems in the nacelle, then the aerodynamic surface and system protection are improved, but the maintenance time and operational efficiency deteriorate
Solution Approach 1:
The cover system is segmented into a fixed cover and a movable hinged cover, allowing selective access to different areas. The hinged cover can be opened independently to access systems at the joint between the attachment strut and engine, while the fixed cover remains closed to maintain aerodynamic integrity.
Solution Approach 2:
The cover transitions from a static fastened design to a dynamic hinged design. The hinged cover can rotate between a closed position (maintaining aerodynamic surface) and an open position (providing access to systems), enabling rapid maintenance operations without removing multiple covers.
2Shape
If multiple fastened covers are used to protect systems in the nacelle, then the aerodynamic surface is improved, but the ease of operation and maintenance access deteriorate
Solution Approach 1:
The cover system is divided into fixed and movable portions. The fixed cover maintains the aerodynamic surface, while the hinged cover provides controlled access when needed, combining aerodynamic integrity with maintenance accessibility.
Solution Approach 2:
The hinged cover acts as an intermediary element between the aerodynamic surface and the systems requiring maintenance. It can be opened to access systems at the joint between the attachment strut and engine, then closed to restore the aerodynamic surface.
3Strength
If several fastening screws are used to secure covers, then the structural integrity and system protection are improved, but the device complexity and maintenance procedures worsen
Solution Approach 1:
Multiple fastening screws are extracted and replaced by a hinge system with fewer fastening points. The hinge system maintains structural integrity while reducing the number of fastening components from multiple screws to a simplified hinge mechanism.
Solution Approach 2:
Instead of distributing multiple fastening screws across the entire cover, the hinge system concentrates fastening at specific strategic locations (hinge attachment points), providing sufficient structural integrity with fewer components.
Data Source
AI summary
An aircraft turbine engine assembly including a nacelle structure with a strut attachment zone, a first cover forming an air intake lip, a hinged cover arranged on the nacelle upper portion, between the first cover and the attachment zone, a hinge system of the cover comprising, on either side of a mid-plane of the nacelle, a front rod and a rear rod that are one in front of the other. The two ends of each rod are co-planar, parallel to the mid-plane. A first end of each rod is hinged on the cover. A second end of each rod is hinged on the structure. A locking system is actuatable from the outside of the nacelle between a locked and an unlocked positon. The nacelle comprises at least one cylinder with a first end mounted hinged on the structure and the other end mounted hinged on the cover.