Aircraft Dynamic Load Testing With Constrained Nozzle Force Vectors
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Solution Overview
Problem
Existing methods for testing aircraft structure dynamic response, such as hydraulic jacks and linear actuators, fail to apply a variable force vector over time, and grounding these devices alters the stiffness of the structure, affecting the accuracy of the test results.
Innovation Solution
A dynamic loading testing device with a nozzle system that applies a constrained force vector to the aircraft structure, using a fluid inlet and outlet, and an attachment mechanism to maintain a set orientation, allowing for variable force application over time, simulating the effect of control surface movements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a linear actuator is grounded (fixed to ground) to apply dynamic force to the structure, then the actuator can provide controlled force variation, but the grounding changes the stiffness of the aircraft structure and affects the dynamic response
Solution Approach 1:
The patent introduces a movable carriage that travels along a rail as an intermediary between the fixed ground and the aircraft structure. The linear actuator is mounted on this carriage, allowing it to move with the structure during dynamic testing. This intermediary setup enables the actuator to apply controlled forces without being rigidly grounded, thus preserving the structure's natural dynamic response while maintaining force control capability.
2Force
If a hydraulic jack is used to exert force and then release it, then the structure can be deflected, but the system cannot apply a variable force vector over a period of time
Solution Approach 1:
The patent transforms the static hydraulic jack system into a dynamic one by mounting it on a movable carriage. This allows the force application point to move along the rail, enabling variable force vectors to be applied at different positions and orientations over time. The system can now dynamically adjust not just the magnitude but also the direction and location of applied forces, significantly enhancing adaptability for simulating various flight conditions.
3Adaptability or versatility
If the nozzle force direction is not constrained, then the attachment mechanism has flexibility, but the force vector orientation cannot be maintained at a desired orientation
Solution Approach 1:
The attachment mechanism is segmented into multiple components: a base plate attached to the structure, a vertical rod providing orientation reference, and the nozzle mounted on the carriage. The rail system provides constraints in specific directions while allowing movement in others. This segmentation allows the force vector orientation to be precisely controlled through the geometric relationships between segments, while maintaining flexibility in the overall attachment configuration.
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 accurate simulation of dynamic responses by applying predictable and variable force vectors without altering the structure's stiffness, providing a truer test of the aircraft's reaction to control surface movements.
Implementation Method 1
fluid is supplied along the length of conduit to the nozzle inlet and ejected from the nozzle outlet such that the nozzle exerts a dynamic force on the aircraft structure in the direction of the nozzle force direction
Data Source
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AI summary
The invention provides an aircraft structure dynamic loading testing device, including a nozzle 141, 142, an attachment mechanism comprising a first portion 124 attached to the nozzle such that a nozzle force direction 141c is constrained at a set orientation and a second portion 125 for attaching to the aircraft structure 110 and configured to be constrained at a given orientation with respect to the aircraft structure, and a length of conduit 121, 123, wherein, in use, fluid is supplied along the length of conduit to the nozzle and ejected from the nozzle such that the nozzle exerts a dynamic force on the aircraft structure in the direction of the nozzle force direction. The invention also provides a dynamic loading testing device, a kit of parts and methods of dynamic load testing of a structure.