Aircraft Control Surface Skew Detection via Integrated Actuator Sensors
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Solution Overview
Problem
Current systems for monitoring the movement and displacement of aircraft aerodynamic control surfaces, such as trailing edge flaps, face challenges in accurately detecting skew and actuator malfunctions, particularly in non-interconnected electromechanical actuator systems, which can lead to reduced reliability and increased part count.
Innovation Solution
The implementation of a sensor assembly integrated within the actuators, utilizing magnetic or optical sensors to detect the position and movement of linear translation elements, allowing for real-time feedback and error condition detection, including skew and actuator malfunctions, through proportional sensor output analysis.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If external driveline-based position tracking systems are used to monitor control surface movement, then measurement precision is improved, but device complexity and part count increase
Solution Approach 1:
The sensor assembly is merged with the actuator structure, integrating position detection functionality directly into the actuator housing. This eliminates separate external position tracking systems while maintaining measurement precision through direct sensing of linear translation element position.
Solution Approach 2:
The position detection function is extracted from the driveline system and placed directly within the actuator. This removes the need for external driveline-based tracking components while preserving the ability to accurately measure control surface position through direct sensor measurement of the linear translation element.
2Reliability
If multiple sensor systems are used to monitor absolute flap position, flap skew position and actuator performance, then reliability is improved, but device complexity increases
Solution Approach 1:
The sensor assembly within each actuator performs multiple functions: detecting absolute position, detecting skew position, and monitoring actuator performance. This multi-functional approach improves reliability through comprehensive monitoring while reducing overall system complexity by eliminating the need for separate dedicated sensor systems for each function.
Solution Approach 2:
The sensor assembly provides real-time feedback on actuator position and performance to the flight control system. This feedback mechanism enables continuous monitoring of absolute position, skew position, and actuator health, improving system reliability through proactive detection and correction of potential issues.
3Reliability
If two actuators are used for each flap to prevent skew, then reliability is improved, but weight and device complexity increase
Solution Approach 1:
The system replaces mechanical skew prevention mechanisms with electronic sensing and control. Instead of using additional mechanical actuators or linkages to physically prevent skew, the invention uses sensor assemblies to detect skew conditions and provides electronic feedback for correction, significantly reducing weight while maintaining reliability.
Solution Approach 2:
Each actuator is equipped with its own sensor assembly that autonomously monitors its own position and detects skew conditions. This self-service capability allows the system to identify and correct skew issues without requiring additional external monitoring systems or redundant actuators, reducing overall system weight while maintaining 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
This approach enhances the accuracy and reliability of aerodynamic control surface monitoring, reduces part count, and enables weight reduction by eliminating the need for external driveline-based position tracking systems, while maintaining high precision in both interconnected and non-interconnected actuator configurations.
Implementation Method 1
The sensor assembly can include sensors, such as magnetic or optical sensors, that detect a position or movement of the linear translation element
Implementation Method 2
The sensor assembly can include sensors, such as magnetic or optical sensors, that detect a position or movement of the linear translation element
Data Source
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AI summary
Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator (226) receiving a first input and a first linear translation element (232) that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly (238) is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator (228) receives a second input and a second linear translation element (236) moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly (240) is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller (218) generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.