Autonomous Landing Gear Aging Monitor with Adaptive Sampling
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Solution Overview
Problem
Current methods for monitoring the aging of aircraft landing gear are inadequate as they either underestimate the impact of landings due to counting aircraft landings rather than gear landings or require connection to the avionics system, leading to high costs and complex certification processes.
Innovation Solution
An autonomous measuring device mounted on the landing gear with sensors to detect position and measure physical parameters, such as accelerations, temperatures, and pressures, which operates in different sampling frequencies based on the gear's position and stores data for detailed monitoring without needing avionics system connection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If sensors are connected to the avionics system of the aircraft, then measurement precision of landing gear aging is improved, but device complexity and certification difficulty increase
Solution Approach 1:
The system is segmented into an autonomous measuring device that operates independently from the aircraft's avionics system. This device includes its own processing unit, memory, and power management, allowing it to function as a standalone monitoring system without requiring integration with complex aircraft systems.
Solution Approach 2:
The autonomous measuring device is self-sufficient with its own power supply (battery), processing capabilities, and data storage. It autonomously monitors physical parameters, processes the data locally, and manages its own operation without requiring external power or control from the aircraft's avionics system.
2Measurement precision
If sensors are connected to the avionics system of the aircraft, then measurement precision is improved, but ease of operation deteriorates due to extensive certification requirements
Solution Approach 1:
The measuring device is extracted from the aircraft's avionics system entirely. It operates as an independent unit that does not require certification as part of the aircraft's critical systems, thereby simplifying the certification process while maintaining measurement capabilities.
3Measurement precision
If the device operates continuously at high sampling frequency, then measurement precision is improved, but energy consumption increases
Solution Approach 1:
The device employs periodic sampling at varying frequencies based on operational conditions. During critical phases like landing, it samples at high frequency to capture detailed data. During less critical phases, it reduces sampling frequency, thereby maintaining measurement precision when needed while significantly reducing overall energy consumption.
Solution Approach 2:
The sampling frequency is dynamically adjusted based on the landing gear's operational state. The device detects gear position and landing events, then adapts its measurement rate accordingly - high frequency during landings and low frequency during flight or idle periods.
4Measurement precision
If the device monitors detailed physical parameters during all phases, then measurement precision is improved, but loss of energy increases
Solution Approach 1:
The monitoring intensity is localized to specific critical phases rather than being uniform across all operational phases. The device focuses its measurement resources on critical events like landing impact and gear extension/retraction, where detailed data is most valuable for assessing aging, while using minimal monitoring during less critical phases.
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
Enables precise monitoring of landing gear aging, minimizing energy consumption for long-term operation and reducing certification complexities, allowing for remote maintenance without human intervention.
Implementation Method 1
at least one sensor configured to measure physical parameters relating to the aging of the landing gear and at least one sensor configured to detect the position of the landing gear and the landing of the aircraft
Data Source
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AI summary
The present invention relates to a method for monitoring the ageing of a landing gear of an aircraft, implemented by an autonomous measurement device installed on said landing gear and comprising sensors and a memory for storage, and comprising: after a landing of the aircraft, a stand-by step comprising detection by means of said sensors of the position of the landing gear at a first sampling frequency, for as long as the position of the landing gear is detected as vertical; after detection of a horizontal position of the landing gear, a sleep step comprising detection by means of said sensors of the position of the landing gear at least at a second sampling frequency, for as long as the position of the landing gear is detected as horizontal; after detection of a vertical position of the landing gear, a measurement step comprising acquisition by means of said sensors of physical parameters relating to the ageing of the landing gear, and detection of a landing of the aircraft at a third sampling frequency until a predetermined period has expired after a landing has been detected, said third frequency being greater than said second frequencies, and said second frequencies being greater than said first frequency; and storage in said storage memory of measurements relating to the ageing of the landing gear as a function of the measured physical parameters.