Nose Landing Gear Steering Chocks for High-Wind Castering Control
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Solution Overview
Problem
Existing chocks for aircraft nose landing gear are ineffective in preventing castering movement caused by high lateral winds, leading to potential aircraft movement and collision risks.
Innovation Solution
A device comprising first and second chocks designed to fit within spaces in the steering mechanism of the nose landing gear, which engage with hydraulic cylinders to limit steering rotation by compressing when the mechanism turns, thereby preventing excessive castering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional chocks are positioned against the wheels of the nose landing gear, then the aircraft is prevented from moving on the tarmac, but castering movement caused by high lateral winds cannot be prevented
Solution Approach 1:
The chock device is divided into multiple independent chocks (first chock and second chock) that can be positioned at different locations. Each chock independently engages with the steering mechanism at specific cylinders, allowing them to work together to prevent castering while maintaining the ability to prevent aircraft movement. This segmentation enables targeted intervention at critical points in the steering mechanism.
Solution Approach 2:
The chocks act as intermediary elements between the steering mechanism and the external environment. By positioning the chocks within the steering mechanism at the cylinders, they serve as mediators that transmit and resist the forces attempting to cause castering, while allowing the wheel to remain chocked against the tarmac for preventing aircraft movement.
2Object-affected harmful factors
If chocks are designed with various shapes and sizes or tied together to prevent castering, then castering may be reduced, but the device complexity and safety are compromised
Solution Approach 1:
Each chock is designed with specific local qualities suited to its position and function. The first chock engages with the first cylinder while the second chock engages with the second cylinder, with each chock having dimensions and structural features optimized for its specific location in the steering mechanism. This local optimization simplifies the overall design compared to complex tied-together configurations while effectively preventing castering.
3Object-affected harmful factors
If sandbags are used as chocks, then castering may be prevented, but the reliability and safety are compromised
Solution Approach 1:
The chocks are designed with specific physical parameters (dimensions, material properties, structural features) that optimize their performance. The chocks have calculated dimensions to fit within the steering mechanism spaces and engage properly with the cylinders, and are made from materials that provide the necessary strength and durability. This parameter optimization ensures both effective castering prevention and high reliability, unlike sandbags which lack controlled parameters.
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
Effectively limits steering rotation of the nose landing gear, keeping the aircraft stationary during high winds, reducing the risk of collision and damage.
Implementation Method 1
The first chock is configured to engage with the first cylinder and to compress to prevent retraction of the first cylinder beyond a first predetermined length. The second chock is configured to engage with the second cylinder and to compress to prevent retraction of the second cylinder beyond a second predetermined length.
Data Source
AI summary
A device to engage with a steering mechanism of a nose landing gear of an aircraft to limit steering rotation of the nose landing gear. The device includes a first chock sized to fit within a first space formed in the nose landing gear at a first cylinder of a steering mechanism, and a second chock sized to fit within a second space formed in the nose landing gear at a second cylinder. The first chock is configured to engage with the first cylinder and to compress to prevent retraction of the first cylinder beyond a first predetermined length. The second chock is configured to engage with the second cylinder and to compress to prevent retraction of the second cylinder beyond a second predetermined length.