Electromechanical Actuating Assembly with Dual Motor Redundancy
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Solution Overview
Problem
Aircraft control-surface actuating assemblies face challenges in maintaining consistent performance during normal and non-normal flight conditions, particularly in scenarios where actuator control is lost or power is compromised, requiring a redundant and fault-tolerant design to ensure reliable operation.
Innovation Solution
An electromechanical actuating assembly with dual electric motors powered by different sources, coupled with decoupling mechanisms and predisposition devices that allow for reversible decoupling and pre-flight testing, enabling the assembly to survive power losses and maintain control-surface components in an optimal position after loss of power.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a redundant design with dual electric motors is implemented, then reliability is improved, but device complexity increases
Solution Approach 1:
The actuating assembly is divided into two independent motor systems (first motor 300A with first drive train 400A, and second motor 300B with second drive train 400B), each capable of independently actuating the control surface. This segmentation allows the system to maintain reliability through redundancy while managing complexity by creating modular, interchangeable subsystems.
Solution Approach 2:
The decoupling mechanisms are pre-configured and ready to disengage failed drive trains before they can cause damage or interfere with the operational motor. The predisposition device is pre-set to automatically position the control surface in a safe state upon detection of motor failure, eliminating the need for complex real-time decision-making algorithms.
2Reliability
If decoupling mechanisms are added to handle motor failure, then reliability is improved, but device complexity increases
Solution Approach 1:
Decoupling mechanisms act as intermediaries between the two motor systems and the actuator. When one motor fails, its decoupling mechanism disengages that motor's drive train from the actuator, preventing interference with the operational motor while maintaining a relatively simple overall architecture.
Solution Approach 2:
The decoupling mechanisms are designed to automatically detect and respond to motor failures without requiring complex external control systems. The mechanisms self-activate upon failure conditions, reducing the need for additional sensors, controllers, and decision-making logic.
3Ease of operation
If predisposition devices are implemented for automatic positioning, then ease of operation is improved, but device complexity increases
Solution Approach 1:
The predisposition device automatically positions the actuator in a predetermined safe position upon detection of motor failure, without requiring pilot intervention or complex control algorithms. This self-service capability simplifies operation while the added complexity is confined to the mechanical positioning mechanism itself.
Solution Approach 2:
The predisposition device is pre-configured with predetermined safe positions for the control surface. Upon motor failure, the device automatically executes the positioning action without requiring real-time calculations or complex decision-making, thereby improving ease of operation with minimal added complexity.
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 redundant design ensures consistent and reliable movement of aircraft control-surface components, even in fault-tolerant modes, by providing decoupling power and maintaining the actuator in an optimal position during power loss, thereby ensuring quick recovery and control establishment.
Implementation Method 1
a first motor (300A) for providing actuator-moving power to the actuator (200), and a second motor (300B) for providing actuator-moving power
Data Source
AI summary
An electromechanical actuating assembly can have a redundant design with a first electric motor providing actuator-moving power via a first drive train and a second electric motor providing actuator-moving power via a second drive train. A first decoupling train can transmit decoupling power to decouple the first drive train from the actuator and a second decoupling train for transmit decoupling power to decouple the second drive train from the actuator. The assembly is operable in a fault-tolerant mode wherein actuator-moving power is transferred only through one drive train and the other drive train is decoupled from the actuator.