Folding Wing Tip Locking Mechanism with Bias Preload
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Solution Overview
Problem
Conventional locking mechanisms for folding wing tip devices on large passenger aircraft fail to provide secure fastening, leading to play and vibrations due to wear, which compromises the structural integrity and safety during flight.
Innovation Solution
A locking mechanism comprising a locking hook and pin with a biasing device, such as a spring or pneumatic/hydraulic system, that preloads the mechanism to compensate for wear and absorb excess loads, ensuring a secure and vibration-free connection between the wing tip device and the fixed wing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional locking mechanism is used to secure the folding wing tip device, then the device can be locked in the flight configuration, but wear in the locking mechanism results in play and vibrations between the wing tip device and the fixed wing
Solution Approach 1:
The biasing device preloads the locking mechanism by applying a continuous force to maintain engagement between the locking hook and locking pin. This preliminary action compensates for wear before it causes play, ensuring the locking mechanism remains stable and vibration-free throughout its service life
Solution Approach 2:
The biasing device changes the force parameter within the locking mechanism by applying a continuous preload force. This parameter change compensates for dimensional changes due to wear, maintaining the engagement force between locking components and eliminating play and vibrations
2Reliability
If the wing tip device is designed with a locking mechanism, then the device can be securely fastened in flight configuration, but the locking mechanism complexity increases
Solution Approach 1:
The biasing device is integrated within the existing locking mechanism structure, nesting the spring component inside the available space between the locking hook and locking pin. This nested arrangement provides the preload function without significantly increasing the overall device complexity or occupying additional external space
Solution Approach 2:
The biasing device is designed as a self-contained spring mechanism that automatically provides preload force without requiring external actuation or control systems. The spring self-generates the necessary force to maintain locking engagement, reducing the need for additional complex control mechanisms
3Reliability
If wear occurs in the locking hook and pin, then the locking mechanism becomes loose, but replacing these components increases maintenance time
Solution Approach 1:
The biasing device provides beforehand cushioning by continuously applying preload force that compensates for wear accumulation. This cushioning effect maintains reliable locking performance throughout the component's service life, delaying the point at which wear requires maintenance and reducing the frequency of replacements
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 provides a secure and stable locking mechanism that maintains the wing tip device in a locked flight configuration, reducing wear-induced play and vibrations, thereby enhancing the structural integrity and safety of the aircraft during flight and ground operations.
Implementation Method 1
The biasing device may be a spring, for example a helical coil spring, a wave spring, or a conical disk spring
Implementation Method 2
The biasing device may be a pneumatic or hydraulic device
Implementation Method 3
The biasing device may be a pneumatic or hydraulic device
Data Source
AI summary
The invention provides an aircraft comprising an aircraft wing. The aircraft wing comprises a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. The aircraft wing further comprises a locking mechanism for locking the folding wing tip device in the flight configuration. The locking mechanism comprises a locking hook associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other of the folding wing tip device and the fixed wing, and a biasing device, wherein in the locked configuration the locking pin is engaged with the locking hook and the biasing device acts to preload the locking mechanism.