Aircraft Landing Gear Locking System with Cam Disk Drive
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Solution Overview
Problem
Current locking systems for aircraft landing gears are complex, require intensive maintenance, and are susceptible to failure due to cable tension variations and the inability of electromechanical units to reset or restart without energy supply.
Innovation Solution
A locking system with an electromechanical drive unit, axle-crossing transmitting means, and a cam disk mechanism that allows for space-efficient torque transmission, featuring redundant electric motors and hydraulic drives for fail-safe operation, along with a spring element for easy retraction and reduced friction resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cable systems are used for mechanical actuation, then the locking system can be activated externally, but the assembly becomes complex and requires intensive maintenance due to multiple deflection pulleys and guideways
Solution Approach 1:
The patent extracts and eliminates the cable system from the locking mechanism, replacing it with a direct electromechanical drive unit that actsuates the locking element without intermediate cable transmissions, pulleys, or guideways. This removes the complex cable routing while maintaining the external activation capability through electrical signals.
Solution Approach 2:
The patent substitutes the mechanical cable actuation system with an electromechanical drive unit that uses electrical motors or actuators to directly move the locking element. This replacement eliminates the need for cable tension management and mechanical transmission components while achieving the same locking and unlocking functions.
2Ease of operation
If traditional electromechanical actuating units are used, then activation is achieved, but they cannot be returned to starting condition by simply shutting off energy supply and are not capable of reset/restart
Solution Approach 1:
The patent implements a dynamic locking element with multiple positional states (locked, unlocked, intermediate) that can transition between states through controlled actuation. The system allows the locking element to be positioned at arbitrary angles along its rotation path, enabling it to return to the starting condition by simply shutting off energy supply and providing reset/restart capability through controlled re-actuation.
Solution Approach 2:
The patent changes the operational parameters of the electromechanical actuating unit by allowing the locking element to operate at variable angular positions rather than fixed binary states. This enables the system to achieve activation at intermediate positions and return to starting conditions by controlling the angular position parameter through the drive unit.
3Reliability
If cable systems with multiple deflection pulleys are used, then external activation is achieved, but the system becomes expensive and susceptible to failure
Solution Approach 1:
The patent extracts and removes the expensive cable system with multiple deflection pulleys and guideways from the locking mechanism. The electromechanical drive unit directly actuates the locking element, eliminating the need for complex cable routing infrastructure and reducing manufacturing costs while maintaining activation reliability.
Solution Approach 2:
The patent substitutes the expensive mechanical cable transmission system with a more economical electromechanical drive unit that uses electrical motors or actuators. This replacement eliminates the need for multiple deflection pulleys, cable tensioners, and guideways, significantly reducing manufacturing complexity and cost while maintaining or improving reliability.
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 system achieves a simple, low-maintenance design with reduced failure probability, enabling safe and efficient locking and unlocking of aircraft landing gears, even in the event of hydraulic system failure, and eliminates the need for separate retracting devices.
Implementation Method 1
a first spring element advantageously is provided, which retracts the cam disk into the neutral position
Implementation Method 2
The first driving device can comprise at least one electric motor
Implementation Method 3
the second driving device can comprise at least one hydraulic drive
Data Source
AI summary
A locking system, in particular a locking system for aircraft landing gears. A space-saving, simple construction and little maintenance requirement of the locking system is achieved by at least one electromechanical drive unit, whose torque is transmitted to a drive shaft with a cam disk via axle-crossing transmitting. With the torque, the cam disk can move the locking system from the locked into the unlocked condition.