Aircraft Engine Pylon Four-Point Articulation Spreader Beam
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Solution Overview
Problem
Existing aircraft engine attachment pylons are complex and bulky due to multiple force paths and redundant safety mechanisms, leading to increased mass and assembly time, particularly in handling thrust force failures.
Innovation Solution
The engine attachment pylon design incorporates a single secondary hinge member that becomes active in case of failure, maintaining a three-point articulation and reducing the lever arm of forces through the articulation member, simplifying the design and eliminating the need for redundant safety paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant safety mechanisms and multiple force paths are integrated into the engine mounting system, then reliability is improved, but device complexity and mass increase
Solution Approach 1:
The patent merges the standby safety function into the existing force transmission path by using the same articulation members and connecting rods. The single force path serves both normal operation and failure compensation, eliminating the need for separate redundant mechanisms while maintaining safety functionality.
Solution Approach 2:
The articulation members and connecting rods are designed to perform multiple functions: they transmit thrust forces during normal operation and automatically compensate for failures by redistributing forces through the same components. This multi-functionality eliminates the need for dedicated standby mechanisms.
2Reliability
If redundant safety mechanisms and multiple force paths are integrated into the engine mounting system, then reliability is improved, but mass increases
Solution Approach 1:
The patent combines the safety compensation function with the existing force transmission components. The same connecting rods and articulation members that transmit thrust during normal operation automatically compensate for failures, eliminating the need for additional mass-dense redundant components.
Solution Approach 2:
The system allows one connecting rod to become inactive (discard its function) during failure, while the other rod recovers by absorbing the full thrust load. This dynamic load redistribution eliminates the need for permanent redundant components that would add mass.
3Reliability
If standby connections are integrated into the rear part of the engine mounting system, then reliability is improved, but assembly time and bulk increase
Solution Approach 1:
The patent merges the standby safety function into the existing single force path structure. The same articulation members and connecting rods serve both normal operation and failure compensation, eliminating the need for separate standby connections that would require additional assembly steps and increase bulk.
Data Source
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AI summary
The invention relates to an aircraft engine attachment pylon comprising a system for mounting the engine (11) including a device (9) for reacting thrust forces which is equipped with two lateral link rods (90) and with a spreader beam (91) mounted in an articulated manner on a support (42) via a main articulation (100) defining a main axis of articulation of the spreader beam (104) positioned in a plane (P). The spreader beam is also mounted in an articulated manner with clearance on the support (42) via a secondary articulation (108) located some distance, when viewed from above, away from the articulation (100) and defining a secondary axis of articulation of the spreader beam (104), also positioned in the plane (P). According to the invention, rotation of the spreader beam is halted by the articulation (108) coming into contact with the spreader beam.