Flight Control Surface Roller Detection Mechanism
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Solution Overview
Problem
Existing flight control surface assemblies for aircraft are complex and costly due to high-reliability mounting structures needed to handle faults like slat skewing, which deviate from predetermined movement paths, and require expensive spherical bearings and multiple links.
Innovation Solution
A flight control surface assembly with a connection assembly, drive arrangement, control unit, rollers, and a detector mechanism that uses a cam surface and biasing mechanism to detect deviations from the predetermined movement path, allowing for simple and cost-effective detection of faults like skewing without increasing weight or complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If high-reliability mounting structures with spherical bearings and multiple links are used to handle fault states, then the reliability is improved, but the device complexity and cost increase
Solution Approach 1:
The patent replaces complex mechanical fault handling structures (spherical bearings, multiple links) with a detection-based approach using sensors and control systems. The sensor arrangement detects fault states like skewing, and the control system manages the response, substituting passive mechanical redundancy with active detection and control.
Solution Approach 2:
The patent introduces a sensor arrangement as an intermediary between the flight control surface and the control system. These sensors detect deviations from the predetermined movement path and transmit information to the control unit, which then manages the fault state without requiring complex mechanical mounting structures.
2Reliability
If high-reliability mounting structures with spherical bearings and multiple links are used to handle fault states, then the reliability is improved, but the weight increases
Solution Approach 1:
The patent replaces heavy mechanical fault handling structures (spherical bearings, multiple links) with lighter sensor and control systems. The detection-based approach eliminates the need for oversized, weighty mounting structures while maintaining reliability through active monitoring and control.
3Device complexity
If detector arrangement is used to detect fault states, then the device complexity is reduced, but the manufacturing precision requirements increase
Solution Approach 1:
The sensor arrangement provides continuous feedback on the position and movement of flight control surfaces. This feedback mechanism allows for real-time detection of deviations from the predetermined movement path, enabling the control system to respond to faults without requiring extremely tight manufacturing tolerances on the mounting structures themselves.
4Ease of manufacture
If detector arrangement is used to detect fault states, then the ease of manufacture is improved, but the measurement precision requirements increase
Solution Approach 1:
The patent substitutes mechanical precision requirements with sensor-based detection. Instead of requiring mechanically precise mounting structures to prevent faults, the system uses sensors to detect faults and control systems to manage them, making the system easier to manufacture while relying on measurement precision for detection.
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 solution effectively detects and prevents deviations from the predetermined movement path, reducing the risk of false alarms from wing bending and enabling reliable detection of skewing, while being lightweight, easy to produce, and maintain, with reduced complexity and cost.
Implementation Method 1
a biasing mechanism (43) which is arranged to bias the first and second rollers (27a, 27b) towards each other
Implementation Method 2
The first axial end face (43a) comprises a cam surface portion (49)
Data Source
AI summary
A flight control surface assembly adapted to be mounted to a main wing of an aircraft includes a flight control surface having a first portion and a second portion spaced from each other, a connection assembly adapted for movably connecting the flight control surface to the main wing, such that the flight control surface is selectively movable in a predetermined movement between a retracted position and an extended position with respect to the main wing, and for each of the flight control surface, a first roller with a first axial face and a second roller with a second axial face facing the first axial face mounted rotatably and coaxially. with a gap between the first and second axial end faces. A biasing mechanism biasing the first and second rollers towards each other, and a transmission mechanism coupled between the flight control surface and the rollers are included.