Aircraft Nozzle Loading Test Rig for True Dynamic Response
Find Innovative SolutionsGenerate Solutions
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 alter 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 nozzle with a fluid inlet and outlet, an attachment mechanism, and a conduit to supply fluid, ensuring the nozzle force direction remains fixed relative to the structure, allowing for variable force application over time.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If a linear actuator is used to apply dynamic force to the aircraft structure, then the force can be applied over a period of time, but the grounding of the actuator changes the stiffness of the structure and affects the dynamic response
Solution Approach 1:
A flexible conduit is introduced as an intermediary between the fluid supply system and the nozzle. This flexible connection allows the nozzle to be positioned at a distance from rigid support structures, preventing the transmission of stiffness to the test structure while maintaining fluid supply to the nozzle for continuous force application.
Solution Approach 2:
The mechanical contact-based linear actuator is replaced with a fluid-based nozzle system that uses fluid momentum to generate force. This substitution eliminates the need for mechanical grounding and direct physical contact with rigid support structures, thereby avoiding stiffness introduction to the test structure.
2Force
If a hydraulic jack is used to exert force on the aircraft structure, then the structure can be deflected, but the jack cannot apply a variable force vector over a period of time
Solution Approach 1:
The nozzle system allows for dynamic control of force magnitude and direction by varying fluid flow parameters. The force vector can be changed in real-time by adjusting fluid pressure and flow rate, enabling the application of variable force vectors over time to simulate different flight conditions and control surface movements.
Solution Approach 2:
The force characteristics are controlled by changing fluid parameters such as pressure, flow rate, and direction. By varying these parameters, the system can generate different force magnitudes and directions, providing the adaptability needed to simulate various operational scenarios on the aircraft structure.
3Stability of the object's composition
If the nozzle force direction is constrained at a fixed orientation, then the force vector orientation is stable, but the device complexity increases due to the attachment mechanism requirements
Solution Approach 1:
The attachment mechanism is divided into separate functional portions: a first portion that attaches to the nozzle and constrains the nozzle force direction, and a second portion that attaches to the aircraft structure. This segmentation allows each portion to be optimized for its specific function while maintaining overall system simplicity.
Solution Approach 2:
The attachment mechanism is designed to provide multiple functions: it secures the nozzle to the structure, constrains the force direction orientation, and allows for easy installation and removal. This multi-functionality reduces the need for additional separate components, thereby managing device complexity while achieving the required orientation stability.
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 forces on aircraft structures, such as those caused by control surface movements, without altering the structure's stiffness, thereby providing a true test of its dynamic response.
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
Implementation Method 2
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
Data Source
AI summary
An aircraft structure dynamic loading testing device, including a nozzle, an attachment mechanism with a first portion attached to the nozzle such that a nozzle force direction is constrained at a set orientation and a second portion for attaching to the aircraft structure and configured to be constrained at a given orientation with respect to the aircraft structure, and a length of conduit. 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. A dynamic loading testing device, a kit of parts and methods of dynamic load testing of a structure are disclosed.