Aircraft Landing Gear Actuator Damping for Abrupt Deployment Stops
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Solution Overview
Problem
Aircraft landing gear undercarriages with electromechanical actuators face damage from sudden stops during deployment due to unregulated speed and shock upon landing, particularly during power failures, which can cause stress on the actuator.
Innovation Solution
An internal damping device is integrated between the output shaft of the electromechanical actuator and the motor shaft to absorb vibrations and shocks, protecting the actuator from damage during sudden stops.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the electromechanical actuator allows free movement to deployed position under gravity, then the landing gear can deploy automatically during power failure, but the actuator arrives at high speed causing abrupt stop and damaging shocks
Solution Approach 1:
A damping device is integrated into the electromechanical actuator to provide beforehand cushioning against shocks. The damping device absorbs impact energy during abrupt stops and vibrations, protecting the actuator components from damage while allowing automatic deployment under gravity to proceed
2Device complexity
If the electromechanical actuator operates without speed regulation, then the structure remains simple, but the actuator cannot control descent speed leading to high-speed arrival and abrupt stopping
Solution Approach 1:
A damping device is introduced as an intermediary element between the motor shaft and output shaft of the electromechanical actuator. This intermediary component provides speed regulation and shock absorption without requiring complex control systems, maintaining relative structural simplicity while enabling controlled descent
3Reliability
If the damping device is added to protect the actuator, then the actuator is protected from shocks, but the device complexity increases
Solution Approach 1:
The damping device is merged with the existing electromechanical actuator structure, integrating protection functionality into the actuator itself rather than adding separate external protection systems. This reduces overall system complexity while providing necessary shock protection
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 damping device effectively reduces the impact of sudden stops and vibrations, safeguarding the electromechanical actuator and ensuring its longevity by regulating the descent speed and absorbing energy during landing.
Implementation Method 1
an internal damping device disposed between an output shaft of the electromechanical actuator coupled to the landing gear and a drive shaft of a motor of the electromechanical actuator
Data Source
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AI summary
A method for protecting against end-of-travel shocks affecting an aircraft landing gear, the landing gear being maneuverable between a retracted position and a deployed position by means of a single electromechanical maneuvering actuator (10) between these two positions. According to the invention, the method comprises the step of equipping the electromechanical maneuvering actuator with an internal shock-absorbing device (17) disposed between an output shaft (18) of the electromechanical actuator coupled to the landing gear and a drive shaft (13) of a motor (12) of the electromechanical actuator.