Aircraft Door Stabilizer Guide Locking for Stable Swiveling
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Solution Overview
Problem
Existing door opening/closing mechanisms in aircraft face instability during the swiveling phase, leading to handling difficulties and potential damage due to increased weight and complexity, particularly when the door is not parallel to the fuselage.
Innovation Solution
A stabilizing rod that translates freely during stop disengagement and locks during swiveling to maintain the door parallel to the fuselage, using a lever and torsion spring mechanism to control its locking and unlocking.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If mass compensation mechanisms and additional articulation arms are used to facilitate door handling, then ease of operation is improved, but weight increases significantly
Solution Approach 1:
The guide rod transitions from a movable state during stop disengagement to a locked state during swiveling, dynamically adapting its function to different phases of door operation. This eliminates the need for permanent mass compensation mechanisms while providing stabilization when needed.
Solution Approach 2:
The guide rod is positioned and locked in advance before the swiveling phase begins, preparing the door for stable rotation. The locking mechanism activates automatically when swiveling starts, ensuring stability is already in place before instability could occur.
2Stability of the object's composition
If two guide rods are used at the top of the door to stabilize during swiveling, then stability is improved, but device complexity increases
Solution Approach 1:
The stabilization function is segmented into different phases: the guide rod is movable during stop disengagement and locked during swiveling. This segmentation allows a single rod to provide stability when needed while remaining simple and unobtrusive during other phases.
Solution Approach 2:
The guide rod system dynamically changes its degrees of freedom based on the door's position and operation phase. The locking mechanism automatically engages/disengages based on the door arm angle, providing stability only when required without adding permanent complexity.
3Object-affected harmful factors
If the door is kept parallel to the fuselage during stop disengagement, then damage prevention is improved, but ease of operation worsens due to required lifting/lowering
Solution Approach 1:
The guide rod is locked in advance before swiveling begins, ensuring the door is properly positioned and stabilized. This preliminary locking action prevents damage during the critical transition phase without requiring the door to be lifted or lowered.
Solution Approach 2:
The guide rod transitions from a constrained movable state to a locked state, dynamically adapting to provide stability during swiveling while allowing freedom of movement during stop disengagement. This eliminates the need for lifting/lowering operations.
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
Stabilizes the door during opening and closing, reducing weight and complexity while preventing damage, and ensuring easy handling without obstructing the door's clear passage or extending into the cabin.
Implementation Method 1
The control means comprises a lever (15) and a torsion spring (16)
Data Source
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AI summary
The invention relates to an assembly for providing stabilising guidance to a semi-plug aircraft door equipped with an opening/closing mechanism. The door frame (3) is provided with stops (7) at the front and at the rear on which the door with its stops (8) bears when it is closed. A door arm (4) links the door (2) to the door frame (3). A guiding connecting rod (6), referred to as a stabilising guiding connecting rod and located on a door edge (2h) extending parallel to the longitudinal axis of the vehicle, is mobile, being able to move in translation at one of its ends in relation to the door in the longitudinal direction of the aircraft during the phases of disengaging and re-engaging the stops (7, 8). During the swivelling and swivelling return phases, the stabilising rod (6) is locked to the door by a lever locking mechanism (9) capable of being actuated by a return means.