Laser Reflection Actuator Feedback for Skew Detection
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Solution Overview
Problem
Current aircraft control surface actuator systems lack efficient feedback mechanisms for monitoring positional accuracy, skew, and actuator malfunction detection, leading to potential control issues during flight maneuvers.
Innovation Solution
An actuator system incorporating dual laser distance sensors within each actuator to provide real-time positional feedback and error condition detection, including skew and malfunction, through proportional analysis of sensor outputs and drive shaft movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple feedback systems with multiple sensors are used to monitor flap deployment and retraction, then measurement precision and reliability are improved, but device complexity and part count increase
Solution Approach 1:
The patent combines multiple feedback functions (absolute position monitoring, skew detection, and actuator malfunction detection) into a single laser-based feedback system. The laser distance sensor measures the position of a reflector attached to the flap, providing comprehensive monitoring data through one integrated sensor rather than multiple separate sensors, thereby reducing part count while maintaining measurement precision
Solution Approach 2:
The laser distance sensor serves multiple functions simultaneously: it measures absolute flap position, detects skew conditions by comparing positions of multiple reflectors, and monitors actuator malfunction by tracking position changes. This multi-functionality eliminates the need for separate sensor systems for each monitoring purpose, reducing overall system complexity
2Reliability
If comprehensive feedback systems with multiple sensors are implemented to detect skew and actuator malfunction, then reliability is improved, but weight increases
Solution Approach 1:
The patent merges multiple monitoring functions (skew detection, position monitoring, malfunction detection) into a single laser feedback system with one laser distance sensor per actuator. This consolidation significantly reduces the number of sensors and associated components required, thereby reducing the overall weight of the actuator system while maintaining comprehensive monitoring capability and high reliability
Solution Approach 2:
The patent replaces traditional mechanical feedback mechanisms (multiple mechanical sensors, linkages, and mechanical position indicators) with an optical laser-based measurement system. This substitution eliminates heavy mechanical components while providing precise measurement capability, resulting in significant weight reduction while improving reliability through more accurate and maintenance-free optical sensing
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
Enhances reliability and reduces part count and weight by providing comprehensive feedback for precise control surface positioning and failure detection, improving aircraft control and safety.
Implementation Method 1
a first laser distance sensor disposed inside the first actuator that generates a first output based on a displacement of the first linear translation element
Data Source
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AI summary
An actuator system (100) for controlling a flight surface of an aircraft (10) includes a first actuator (200) 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 laser distance sensor (212) disposed inside the first actuator (200) that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator (202) 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 laser distance sensor (214) disposed inside the second actuator (202) that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit (102) that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.