Electromechanical Actuator Damping via Motor Load Switching
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Solution Overview
Problem
Existing electromechanical actuators in aircraft primary flight control systems lack an effective damping mechanism, particularly for low-voltage systems, which can lead to uncontrolled movement during malfunctions or power losses.
Innovation Solution
The implementation of control electronics that connect an electric motor to an electric or electronic load and/or deactivate a DC/DC converter, effectively providing a damping function similar to short-circuiting the motor phases, but with improved reliability and compatibility with low-voltage systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If eddy current brakes are used for damping, then damping function is provided, but temperature and vibration conditions in aircraft have detrimental effect on reliability
Solution Approach 1:
The patent replaces mechanical damping elements (eddy current brakes) with an electronic damping system that uses the motor controller and power supply unit to provide damping through electrical means, eliminating the mechanical components that are sensitive to temperature and vibration
Solution Approach 2:
The patent introduces the motor controller and power supply unit as intermediary components that mediate the damping function, using the existing electrical system to provide damping without requiring additional mechanical damping elements that would be affected by environmental conditions
2Reliability
If motor phases are short-circuited by relays, then damping is achieved, but relay life is significantly reduced
Solution Approach 1:
The patent replaces mechanical relay switches with an electronic control system that uses the motor controller and power supply unit to short-circuit motor phases electronically, eliminating mechanical wear and extending component life
Solution Approach 2:
The patent utilizes the existing motor controller and power supply unit to provide the damping function, allowing these components to serve dual purposes (motor control and damping) without requiring additional dedicated components that would have limited lifespan
3Reliability
If hydraulic bypass is used for damping, then damping function is provided, but system complexity increases
Solution Approach 1:
The patent merges the damping function with the existing motor controller and power supply unit, combining multiple functions into already-present components rather than adding separate hydraulic damping systems
Solution Approach 2:
The patent makes the motor controller and power supply unit multi-functional by using them both for their primary purpose (motor control and power conversion) and for providing the damping function, eliminating the need for dedicated damping components
4Reliability
If DC/DC converter is deactivated, then damping is achieved, but power supply to motor is interrupted
Solution Approach 1:
The patent dynamically controls the DC/DC converter, activating it during normal operation to supply power to the motor and deactivating it only when damping is required, allowing the system to adapt its power supply state based on operational needs
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 provides an effective electronic damping mechanism for electromechanical actuators in aircraft, ensuring controlled movement even during electrical failures or power losses, while being compatible with existing components and low-voltage systems.
Implementation Method 1
the control electronics comprise detection means for detecting the counter voltage of the electric motor or that the control electronics are supplied with the counter voltage of the electric motor
Implementation Method 2
the control electronics can connect or connects an electric motor, preferably of the electromechanical actuator, to an electric or electronic load
Data Source
AI summary
The present invention relates to control electronics, preferably for an electromechanical actuator, preferably for use in a primary flight control system of an aircraft, wherein the control electronics can connect or connects an electric motor, preferably of the electromechanical actuator, to an electrical or electronic load and/or wherein the control electronics can deactivate or deactivates a DC/DC converter supplying electrical power to the electric motor, and to an electromechanical actuator and to a method for damping the movement of an electromechanical actuator.