Aircraft Electromechanical Brake Vibration Reduction via Non-Uniform Actuator Force
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Solution Overview
Problem
Electromechanical brakes in aircraft generate significant vibrations during braking operations, leading to reliability concerns and mechanical stress on landing gear and equipment, with existing solutions increasing complexity and cost by breaking structural symmetry.
Innovation Solution
Distributing the total braking force non-uniformly among the actuators of the brake, allowing at least two actuators to apply different forces, thereby decoupling vibration modes and reducing generated vibration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If the symmetry of the brake structure is broken by adding openings or recesses, then vibration modes are attenuated, but the structure becomes more complex and weight increases
Solution Approach 1:
The patent applies asymmetry by distributing braking forces in non-uniform manner among actuators rather than symmetrically. This breaks the symmetry of forces applied to friction members, which decouples vibration modes and reduces vibration levels without requiring structural modifications like openings or recesses.
Solution Approach 2:
The patent changes the parameter of force distribution from uniform to non-uniform among actuators. By varying the braking force parameters applied by different actuators during a braking operation, the system achieves vibration reduction through control parameter optimization rather than structural modification.
2Object-affected harmful factors
If the symmetry of the brake structure is broken by adding openings or recesses, then vibration modes are attenuated, but the weight of the brake increases
Solution Approach 1:
The patent applies asymmetry by distributing braking forces in non-uniform manner among actuators rather than symmetrically. This breaks the symmetry of forces applied to friction members, which decouples vibration modes and reduces vibration levels without requiring structural modifications like openings or recesses.
Solution Approach 2:
The patent changes the parameter of force distribution from uniform to non-uniform among actuators. By varying the braking force parameters applied by different actuators during a braking operation, the system achieves vibration reduction through control parameter optimization rather than structural modification.
3Device complexity
If uniform braking force is applied by all actuators, then the brake structure remains simple and lightweight, but high vibration levels are generated
Solution Approach 1:
The patent applies asymmetry by distributing braking forces in non-uniform manner among actuators rather than symmetrically. This breaks the symmetry of forces applied to friction members, which decouples vibration modes and reduces vibration levels without requiring structural modifications like openings or recesses.
Solution Approach 2:
The patent changes the parameter of force distribution from uniform to non-uniform among actuators. By varying the braking force parameters applied by different actuators during a braking operation, the system achieves vibration reduction through control parameter optimization rather than structural modification.
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
Significantly reduces vibration levels during braking operations without increasing the complexity or weight of the brake structure, ensuring uniform wear and reliability.
Implementation Method 1
friction at the interfaces between the carbon disks give rise to vibration
Implementation Method 2
By distributing the total force in non-uniform manner among the actuators, the symmetry of the forces applied against the friction members is broken, thereby enabling vibration modes to be decoupled, and thus reducing the level of the vibration that is generated during a braking operation
Data Source
AI summary
The invention relates to an electromechanical braking method for an aircraft having at least one electromechanical brake 2 fitted to at least one braked wheel 1 of the aircraft, the brake 2 having friction members 3 and a plurality of electromechanical actuators 4, each actuator 4 comprising a pusher 5 suitable for being moved by means of an electric motor 6 to selectively apply a pressing force on the friction members 3. According to the invention, for a given braking operation, a total braking force to be applied against the friction members 3 of the brake is distributed in non-uniform manner amongst the actuators 4 of the brake, such that at least two actuators 4 apply respective different forces.