Tiltable Linear Actuator for Aircraft Part Load Testing
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Solution Overview
Problem
Current load testing apparatuses for aircraft parts lack the necessary precision and reliability to meet stringent design tolerance requirements, particularly in terms of weight reduction and cost efficiency.
Innovation Solution
An apparatus comprising a linear actuator with a tiltable first part pivotally constrained about orthogonal axes, a load cell to measure force along a longitudinal direction, clinometers to measure rotation angles, and a displacement transducer to measure sliding, allowing for improved accuracy in load testing by applying and measuring forces and deformations in multiple directions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional load testing apparatuses are used, then the testing can be performed, but the precision and reliability are insufficient to meet stringent design tolerance requirements
Solution Approach 1:
The patent applies dimensionality change by introducing a tiltable linear actuator that can rotate about orthogonal axes (first and second geometric axes), transforming a single-axis measurement system into a multi-dimensional measurement system. The first and second clinometers measure rotation angles about these orthogonal axes respectively, enabling the system to capture deformation data from multiple spatial dimensions simultaneously, thereby improving both measurement precision and reliability for complex structural deformations
Solution Approach 2:
The patent uses clinometers as intermediary devices between the linear actuator and the measurement system. These clinometers act as mediators that convert the complex multi-axis rotation and deformation of the actuator into measurable angular parameters, enabling indirect but accurate measurement of structural properties that would be difficult to measure directly
2Weight of moving object
If weight-saving capacity is increased to reduce costs, then cost efficiency improves, but the accuracy of load tests may be compromised
Solution Approach 1:
The linear actuator serves multiple functions: it applies test loads, measures forces via the load cell, measures rotation angles via two clinometers mounted at different positions, and measures sliding displacement via the displacement transducer. This multi-functionality allows a single device to provide comprehensive measurement data (force, angle, displacement) needed for accurate load testing, maintaining measurement precision while potentially reducing the need for multiple separate heavy measurement devices
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 the accuracy of load tests by enabling precise measurement of forces and deformations, allowing for better estimation of structural properties and optimization of aircraft parts, including stiffness, deformation energy, and natural frequencies, while improving the efficiency of load verification and constraint reactions.
Implementation Method 1
a load cell, mounted on the second part of the linear actuator and interposed between the latter and the aircraft part to measure a force acting on the aircraft part along said longitudinal direction
Implementation Method 2
a first and a second clinometer, mounted on the linear actuator, each adapted to measure a respective angle representative of the rotation of the linear actuator about the first and second geometric axes respectively
Implementation Method 3
a displacement transducer, mounted on the first part of the linear actuator, and adapted to measure the sliding of the second part of the linear actuator relative to the first part of the linear actuator
Data Source
AI summary
An apparatus for carrying out load testing on an aircraft part is described. In one aspect, the apparatus includes means for constraining the aircraft part and a linear actuator for applying a test load. The linear actuator has a first part being tiltable and being pivotally constrained about a first and a second geometrical axes, orthogonal to one another, and a second part being slidably mounted on the first part to slide along a longitudinal direction. A load cell, mounted on the second part, measures force acting on the aircraft part along the longitudinal direction. In one aspect, a first clinometer and a second clinometer are mounted on the linear actuator, each clinometer measuring a respective angle representative of rotation of the linear actuator respectively about the first and second geometrical axes. A displacement transducer measures sliding of the second part relative to the first part of the linear actuator.