Aircraft Actuator Skew Detection via Dual Sensor Feedback
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Solution Overview
Problem
Current aircraft trailing edge flap systems lack a comprehensive solution for monitoring positional accuracy, skew detection, and actuator malfunction identification, leading to potential control issues during flight maneuvers.
Innovation Solution
An actuator system with dual sensors and a control unit that monitors the displacement of linear translation elements, determining error conditions such as skew and actuator malfunctions by comparing sensor outputs and drive shaft rotation, allowing for integrated feedback and failure detection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple separate feedback systems are used to monitor flap deployment, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The patent combines multiple feedback functions (absolute position monitoring, skew detection, and actuator failure detection) into a single integrated sensor system. Each actuator includes one sensor that simultaneously provides all three types of monitoring information, eliminating the need for multiple separate feedback systems while maintaining comprehensive measurement precision.
Solution Approach 2:
The sensor system is designed to perform multiple functions simultaneously: measuring absolute flap position, detecting skew conditions by comparing positions of multiple actuators, and identifying actuator failures through position discrepancies. This multi-functional approach reduces system complexity while improving overall monitoring capability.
2Measurement precision
If separate systems are used for positional feedback, skew detection, and failure detection, then measurement precision is improved, but weight increases
Solution Approach 1:
The patent merges multiple monitoring functions into a single sensor unit per actuator, eliminating redundant components that would add weight. The integrated system provides positional feedback, skew detection, and failure detection without requiring separate sensor systems for each function.
Solution Approach 2:
Each sensor in the system is designed to perform multiple monitoring tasks simultaneously, reducing the total number of sensors and associated hardware needed. This multi-functional design directly reduces the overall weight of the actuator system while maintaining comprehensive monitoring precision.
3Reliability
If multiple actuators are used for each flap side, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent implements a feedback mechanism where sensors on each actuator continuously monitor their own position and the position of opposing actuators. The control system compares these positions to detect skew conditions and potential failures, providing real-time feedback that enhances reliability while managing system complexity through intelligent monitoring.
Solution Approach 2:
The control system acts as an intermediary that processes information from multiple sensors and actuators, comparing positions and detecting discrepancies. This intermediary function coordinates the multiple actuators, ensuring they work together reliably while simplifying the overall system architecture through centralized intelligence.
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 provides reduced part count, weight, and improved reliability by integrating positional feedback, skew detection, and failure detection, enhancing aircraft control surface management and reducing the risk of malfunctions.
Implementation Method 1
a first linear translation element (208) that moves based on rotational motion received at the first actuator input
Data Source
AI summary
An actuator system for controlling a flight surface of an aircraft includes a first actuator having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first sensor coupled to the first linear translation element that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second sensor coupled to the second linear translation element that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.