Aircraft Cowl Deployment Mechanism on Longitudinal Spar
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Solution Overview
Problem
Existing deployment mechanisms for aircraft turbofan engine fairing covers face mechanical stress and geometric restrictions when mounted directly on the gas generator casing or connected to a pylon, limiting their functionality and accessibility for inspection and maintenance.
Innovation Solution
A deployment mechanism is mounted on a longitudinal beam parallel to the turbojet's longitudinal axis, featuring a pivoting arm and a holding rod with sliding articulations, allowing the fairing cover to be opened and closed without mechanical interference, and maintained in position using a deformable parallelogram configuration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the deployment mechanism is mounted directly on the gas generator casing, then the mechanism can be integrated with the engine structure, but the casing is subjected to additional mechanical stresses that should be avoided
Solution Approach 1:
The patent introduces a pylon as an intermediary structure between the deployment mechanism and the gas generator casing. The deployment mechanism is mounted on the pylon rather than directly on the casing, allowing the pylon to absorb and transmit mechanical stresses away from the gas generator casing, thus resolving the contradiction between integration and stress avoidance.
2Stress or pressure
If the deployment mechanism is connected to a pylon supporting the propulsion assembly, then the gas generator casing is protected from additional mechanical stresses, but the geometry, size and kinematics of the deployment mechanism are restricted to avoid mechanical interference
Solution Approach 1:
The deployment mechanism is segmented into multiple independent components: a deployment arm for actuating the fairing cover, a holding arm for maintaining position, and a actuating arm connected to the control cable. This segmentation allows each component to be optimized independently, reducing geometric and kinematic restrictions while maintaining protection of the gas generator casing.
3Ease of operation
If the fairing cover is opened for inspection and maintenance, then access to the gas generator is improved, but the deployment mechanism must accommodate additional spatial requirements for operation
Solution Approach 1:
The deployment mechanism employs dynamic arms that can pivot and extend as needed. The deployment arm rotates about a pivot point to open the fairing cover, and the holding arm can extend to maintain the open position. This dynamic design allows the mechanism to provide adequate access space only when needed, rather than permanently occupying additional space, thus resolving the contradiction between maintenance access and space requirements.
Data Source
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AI summary
The invention relates to the field of aircraft propulsion unit fairings and, more particularly, to an assembly comprising a longitudinal spar (31) configured to be mounted on a lateral member of a bypass turbojet engine (7) gas generator (11), which spar is oriented parallel to a longitudinal axis (X) of the bypass turbojet engine (7), an opening cowl (50) of the fairing (18) of the gas generator (11), and a deployment mechanism (60) mounted on the longitudinal spar (31) in order to move the opening cowl (50) between an open position and a closed position.