Aircraft Engine Mount Hinge Pin Locking Assembly
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Solution Overview
Problem
Existing aircraft engine mount assemblies suffer from significant offset and bulk due to the stacking of locking components, which complicates assembly and increases mass, affecting compactness and ease of use.
Innovation Solution
A revised assembly design featuring a tubular extension with reduced offset, utilizing an inner elastic stop ring and a dual locking system with a locking screw and wire, which minimizes the bulk and mass of the locking mechanism, allowing for a more compact and efficient engine mount assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a traditional locking device with locking washer, elastic stop ring, and pin is used, then the hinge pin is securely blocked in translation, but the offset and bulk increase significantly
Solution Approach 1:
The patent combines multiple locking functions into a single integrated locking device that performs both translation blocking and rotation locking simultaneously. The locking device integrates the functions previously performed by separate components (locking washer, elastic stop ring, pin) into one unified structure, eliminating the need for stacked components and reducing overall offset.
Solution Approach 2:
The locking device is designed to perform multiple functions: blocking translation in the second direction, preventing rotation of the hinge pin, and providing secure mounting. This multi-functional design eliminates the need for separate dedicated components for each function, thereby reducing the cumulative offset.
2Reliability
If multiple locking components (locking washer, elastic stop ring, pin) are stacked, then the hinge pin is securely immobilized, but the mass and complexity increase
Solution Approach 1:
The patent merges multiple locking components into a single integrated locking device that provides both translation blocking and rotation locking in one unit. This consolidation reduces the number of separate parts from three or more components to a single device, simplifying the assembly and reducing complexity.
Solution Approach 2:
The locking device internally segments its functionality into distinct zones: one for blocking translation and another for preventing rotation. This internal segmentation allows multiple functions to be achieved within a single component rather than requiring multiple separate components.
3Reliability
If a robust locking mechanism with multiple components is used, then the hinge pin remains secure, but the assembly becomes bulkier and harder to install
Solution Approach 1:
By combining multiple locking functions into a single pre-assembled locking device, the patent reduces the number of assembly steps. The integrated device can be installed as one unit rather than requiring sequential assembly of multiple separate components, significantly improving ease of installation while maintaining security.
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 revised assembly achieves a more compact and lightweight design, facilitating easier installation and maintenance while maintaining effective locking functionality, suitable for both new and existing engine mounts.
Implementation Method 1
an external elastic stop ring 54 which is partially housed in an annular groove formed in the rear part 50.2 of the screw 50 making it possible to immobilize the locking washer 52 in the notches 48.2 of the extension 48
Data Source
Figure 1~4
Figure 5~9
AI summary
The invention relates to an assembly for an aircraft engine mount comprising: - a pivot shaft (72) supported by two plain bearings (76, 78), - a locking device that prevents translation of the pivot shaft (72) in a direction comprising: ∘ a locking screw (90) which, during operation, is screwed into a first internal portion (84) threaded into a tubular extension (82) integral with one of the two plain bearings, ∘ a first locking system (106) comprising an internal elastic retaining ring (110) housed in a groove (112) formed in the tubular extension (82), and ∘ a second locking system (108) comprising a locking wire (114) which passes through first holes (116) in the second section (94) of the locking screw (90) and second holes (118) in the tubular extension (82).