Aircraft Door Rotary Link Decoupling Mechanism
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Solution Overview
Problem
Existing connecting mechanisms between aircraft doors and structures fail to provide precise guidance during opening and closing while minimizing mechanical action transmission between the aircraft frame and door, especially when the door is closed, due to residual transmission issues exacerbated by temperature and pressure changes.
Innovation Solution
A rotary link assembly with a shaft that translates and locks into a disengaged position, utilizing ball joints and adjustable support members to decouple the door from the arm, eliminating the need for elastomeric elements and maintaining stiffness for precise guidance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If elastomeric elements are used to decouple the door from the link mechanism, then the transmission of mechanical actions between the framework and the door is reduced, but the guiding precision during opening and closing is degraded
Solution Approach 1:
A decoupling device with a shaft and support members acts as an intermediary between the door and the link mechanism. The shaft can translate along its axis to provide decoupling while the support members maintain guidance precision during operation
Solution Approach 2:
The decoupling device transitions from a static connection to a dynamic system where the shaft can translate and the support members can adjust their position, allowing the system to adapt between guided motion and decoupled states
2Ease of operation
If a deformable parallelogram is used to guide the door, then guidance during docking and withdrawal is provided, but complete decoupling when the door is closed cannot be achieved
Solution Approach 1:
The connection system is segmented into distinct functional components: the link mechanism for guidance, the decoupling device with shaft for decoupling, and support members for maintaining position. This segmentation allows each component to perform its specific function without compromising the others
3Reliability
If elastomeric dampers are used for decoupling, then mechanical action transmission is reduced, but the decoupling effectiveness varies with temperature and pressure
Solution Approach 1:
The patent replaces elastomeric mechanical elements with a mechanical decoupling device using a shaft, support members, and ball joints. This substitution eliminates temperature and pressure sensitivity while maintaining effective decoupling of mechanical actions
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 solution achieves complete mechanical decoupling between the aircraft frame and door in the closed position, maintaining precise guidance and stiffness during opening and closing, independent of temperature and pressure variations, without degrading mechanical guidance or introducing elastomeric losses.
Implementation Method 1
a ball joint (66, 68) between the door (16) and each end of the shaft (42)
Implementation Method 2
an element (46) for elastic biasing of the shaft (42)
Data Source
Figure 1
Figure 2
Figure 3~5
AI summary
The linking mechanism (18) comprises an arm (30) intended to be articulated on the structure (12), and a rotating linkage assembly (32) between the door and the arm (30). The rotating linkage assembly (32) can be disengaged from a configuration of the door linked to the arm (30) in an open position of the door, to a configuration of the door disengaged from the arm (30) in a closed position of the door.