Flight Control Surface Load Testing Apparatus
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Solution Overview
Problem
Current load testing methods for aircraft control surfaces require repositioning and reconfiguration of load structures, leading to increased downtime and testing time, as torque and tensile/compressive forces are not independently controllable, affecting the efficiency of static and fatigue tests.
Innovation Solution
A load testing apparatus with vertically and fore/aft load structures that apply torque and tensile/compressive forces independently, using rubber pads and actuators to simulate forces without inducing moment arms, allowing for simultaneous and varied force applications without repositioning the structures or flight control surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional load testing methods are used with single-directional load structures, then the testing setup is simpler, but repositioning and reconfiguration are required for different force applications, increasing downtime and testing time
Solution Approach 1:
The load testing apparatus is segmented into multiple independent load structures: vertical load structures for applying torque and fore/aft load structures for applying tensile/compressive forces. Each structure can be independently controlled and positioned, eliminating the need to reconfigure the entire system for different force applications. This segmentation allows simultaneous application of multiple force types without repositioning.
Solution Approach 2:
The invention introduces multi-directional load structures that operate in different spatial dimensions. Vertical load structures apply forces in the vertical direction to create torque, while fore/aft load structures apply forces in the forward/aft direction for tensile/compressive loading. By adding dimensional diversity to the load application system, the apparatus can independently control multiple force components without reconfiguration.
2Adaptability or versatility
If torque and tensile/compressive forces are applied using the same load structure, then the device complexity is reduced, but the forces are not independently controllable, requiring repositioning for different test conditions
Solution Approach 1:
The load testing apparatus is segmented into multiple independent load structures: vertical load structures for applying torque and fore/aft load structures for applying tensile/compressive forces. Each structure can be independently controlled and positioned, eliminating the need to reconfigure the entire system for different force applications. This segmentation allows simultaneous application of multiple force types without repositioning.
Solution Approach 2:
Each load structure is designed with universal functionality to handle different force applications. The vertical load structures can apply torque through compressive forces, while the fore/aft load structures can apply both tensile and compressive forces. This multi-functionality at the component level reduces the overall device complexity by eliminating the need for specialized structures for each force type.
3Measurement precision
If load structures are repositioned for different force intensities and directions, then measurement precision is improved, but testing time and operational efficiency decrease
Solution Approach 1:
The load structures are pre-positioned in optimal locations before testing begins. The vertical load structures are positioned to apply torque at the appropriate moment arm distance from the hinge line, and the fore/aft load structures are positioned to apply tensile/compressive forces at the correct locations on the control surface. This preliminary positioning eliminates the need for repositioning during different test phases while maintaining measurement precision.
Solution Approach 2:
The load structures are designed to be dynamically adjustable in force magnitude while maintaining fixed positions. actuators can vary the force intensity applied by each load structure without requiring physical repositioning. This dynamic force control allows precise application of different force intensities and directions while maintaining high testing throughput.
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
Enables efficient load testing by decoupling torque and tensile/compressive forces, reducing downtime and overall testing time, as hundreds or thousands of force intensities can be applied contemporaneously during static or fatigue tests, identifying structural weaknesses without reconfiguring the setup.
Implementation Method 1
a first rubber pad having a surface extending in a first plane that is arranged to contact a lower surface of the flight control surface
Implementation Method 2
Each of the plurality of fore/aft load structures can include a first rubber pad
Data Source
AI summary
A load testing apparatus can include a plurality of vertical load structures arranged on a flight control surface to provide torque on the control surface and reacted by a control rod of the flight control surface. The load testing apparatus can also include a plurality of fore/aft load structures arranged to provide tensile and/or compressive force in a direction intersecting a hinge line of the flight control surface. Each of the plurality of fore/aft load structure can include a first rubber pad having a surface extending in a first plane that is arranged to contact a lower surface of the flight control surface. Each of the plurality of fore/aft load structures can also include a first rubber pad having a surface extending in a second plane that is arranged to contact an upper surface of the flight control surface, wherein the first plane and the second plane are non-parallel planes.