Aircraft Landing Gear Locking Bolt Merging Uplock Downlock Functions
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Solution Overview
Problem
Conventional aircraft landing gear locking systems require multiple components and increased weight, leading to higher fuel consumption due to the need for separate uplock and downlock mechanisms, which occupy significant installation space.
Innovation Solution
A locking device with a movably arranged locking bolt within a locking cylinder that secures the landing gear in both retracted and extended positions, eliminating the need for separate uplock and downlock units, and incorporating redundant spring pretensioning and motorized mechanisms for enhanced reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate uplock and downlock mechanisms are used to secure landing gear in retracted and extended positions, then reliability of gear positioning is improved, but device complexity and installation space requirements increase
Solution Approach 1:
The patent merges the previously separate uplock and downlock mechanisms into a single integrated locking device. The locking bolt can be positioned in multiple locked states (first locked state for retracted position, second locked state for extended position) while remaining part of one unified mechanism mounted on the landing gear leg. This consolidation maintains the reliability of gear positioning in both states while reducing device complexity and installation space requirements.
Solution Approach 2:
The locking bolt is designed as a universal component that performs multiple functions: it secures the landing gear in the retracted position (first locked state) and also secures it in the extended position (second locked state). This multi-functional design eliminates the need for separate specialized components for each position, thereby reducing overall system complexity while maintaining reliable positioning in both states.
2Reliability
If separate uplock and downlock mechanisms are provided, then gear positioning reliability is improved, but aircraft weight increases
Solution Approach 1:
By combining the uplock and downlock functions into a single locking device with one locking bolt, the total weight of the locking system is reduced compared to having separate mechanisms. This weight reduction directly decreases aircraft weight while maintaining the reliability of gear positioning in both retracted and extended states through the bolt's multiple locked positions.
3Reliability
If multiple locking components are used for uplock and downlock, then security of gear positioning is improved, but fuel consumption increases
Solution Approach 1:
The integration of uplock and downlock functions into a single locking device reduces the total weight of the landing gear system. This weight reduction decreases the energy required for landing gear operations and overall aircraft movement, thereby reducing fuel consumption while maintaining secure gear positioning through the locking bolt's multiple locked states.
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
This solution reduces the number of components and installation space, decreases aircraft weight, and enhances operational efficiency by simplifying the locking mechanism while ensuring reliable gear positioning and safety through redundant systems.
Implementation Method 1
The locking bolt is pretensioned by an elastic element, preferably a spring or the like
Data Source
AI summary
A locking device of an aircraft landing gear for locking the landing gear in a retracted and an extended position. A locking cylinder is arranged on a landing gear leg and a locking bolt is movably arranged in the locking cylinder. In the retracted position and in the extended position of the landing gear the locking bolt serves to fix the landing gear leg.