Remote Angle Calibration for Aircraft Members Using Magnetometer
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Solution Overview
Problem
Current systems for testing the angular movement of aircraft members are prone to alignment errors and safety hazards due to the use of large mass linkages and manual measurement requirements, which can lead to inaccurate results and pose risks to technicians during testing.
Innovation Solution
A method and device utilizing a multi-axis angle measurement device with gyro sensors to calculate the angular deflection of aircraft members by obtaining initial and dynamic values, calculating compensated values, identifying the axis of rotation, and integrating rates to determine the angle of deflection, while allowing for wireless transmission of calculations and alignment with a known angle, enabling precise and safe measurement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If linkages with angle sensors are used to measure aircraft member movement, then the angular position can be detected, but alignment errors occur due to inherent misalignment of linkages relative to the flight control surface
Solution Approach 1:
The patent replaces the mechanical linkage system with a magnetometer-based measurement system. The magnetometer senses the magnetic field generated by a permanent magnet attached to the aircraft member, eliminating the need for physical linkages and their associated alignment errors. This substitution of mechanical sensing with magnetic field sensing directly resolves the alignment precision problem.
Solution Approach 2:
The patent introduces a permanent magnet as an intermediary between the aircraft member and the magnetometer. The magnet creates a magnetic field that serves as the measurement medium, allowing angular position detection without direct mechanical contact or alignment between the measurement device and the aircraft member.
2Measurement precision
If pendulous accelerometers are used to sense angle change, then angle measurement can be achieved, but the system complexity increases and alignment requirements become more stringent
Solution Approach 1:
The patent replaces pendulous accelerometers with a magnetometer system. Instead of using mechanical acceleration sensing that requires complex mounting and alignment, the magnetometer measures angular position directly through magnetic field sensing, simplifying the overall system architecture while maintaining measurement capability.
3Measurement precision
If manual testing is performed with a technician at the aircraft member, then direct measurement is possible, but safety hazards arise due to the moving aircraft member posing risk to the technician
Solution Approach 1:
The measurement system is attached to the aircraft member itself, allowing the device to measure its own angular position during movement. This self-measuring capability eliminates the need for external technicians to be present at the moving component, thereby removing the safety hazard while maintaining accurate measurement.
Solution Approach 2:
The magnetometer and permanent magnet system serve as an intermediary measurement mechanism that can operate remotely and safely. The magnetic field transmission allows measurement without direct human contact with the moving aircraft member, resolving the safety issue.
4Strength
If linkages with large mass are used for measurement, then the linkage structure can be rigid, but it becomes difficult to accurately attach to the flight control surface
Solution Approach 1:
The patent replaces the rigid mechanical linkage with a magnetic field-based sensing system. The magnetometer and permanent magnet configuration eliminates the need for heavy, rigid linkages, allowing for lightweight attachment to the flight control surface while maintaining measurement accuracy.
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 provides accurate and safe measurement of angular deflection of aircraft members, reducing alignment errors and safety risks by using a multi-axis angle measurement device with gyro sensors to calculate compensated dynamic values and determine the axis of rotation, resulting in precise and reliable angular position determination.
Implementation Method 1
A magnetometer measures a magnetic field generated by a permanent magnet attached to the aircraft member
Implementation Method 2
A device utilizes a multi-axis angle measurement device with gyro sensors to calculate the angular deflection of aircraft members
Data Source
AI summary
Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.