Servo Actuator Test Bench for Dynamic Load Simulation
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Solution Overview
Problem
Existing test benches for simulating dynamic loads on actuators are time-consuming and complex to set up for each flight point, making it difficult to efficiently replicate the aerodynamic loads experienced by aircraft components during operation.
Innovation Solution
A test bench equipped with a force actuator, pressure sensors, and a closed-loop control system that adjusts dynamic loads based on measured pressure, allowing for precise control and rapid simulation of aerodynamic loads similar to those encountered in aircraft operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a mechanical spring and damping actuator are used to generate dynamic loads, then the test bench can simulate aerodynamic loads on actuators, but the setup process becomes time-consuming and complex for each flight point
Solution Approach 1:
The patent replaces the mechanical spring and damping actuator system with a servo actuator that uses controlled fluid pressure to generate dynamic loads. This substitution allows for programmable control of load characteristics, eliminating the need for manual mechanical reconfiguration when changing test parameters, thus reducing setup time while maintaining simulation accuracy
Solution Approach 2:
The patent enables dynamic load simulation by changing fluid pressure parameters controlled by a servo valve rather than physically reconfiguring mechanical components. The servo actuator can programmatically adjust pressure, force magnitude, and oscillation frequency, allowing rapid transition between different flight points without time-consuming mechanical setup changes
2Adaptability or versatility
If mechanical springs and dampers are configured to adjust oscillation frequency and damping, then dynamic load characteristics can be controlled, but the device complexity increases
Solution Approach 1:
The patent replaces complex mechanical spring-damper systems with a servo actuator controlled by fluid pressure. This substitution simplifies the overall device architecture by eliminating multiple mechanical components (springs, dampers, linkages) while maintaining or enhancing load control capability through electronic control of the servo valve, thereby reducing device complexity
Solution Approach 2:
The patent introduces a servo valve as an intermediary component that controls fluid pressure to the servo actuator. This intermediary enables precise control of dynamic load characteristics (force magnitude, frequency, damping) through electronic signals rather than direct mechanical adjustment, simplifying the control architecture while maintaining adaptability
3Reliability
If multiple flight points are simulated using mechanical reconfiguration, then comprehensive actuator validation is achieved, but the testing process becomes excessively time-consuming
Solution Approach 1:
The patent replaces mechanical reconfiguration with programmable servo actuator control, enabling rapid switching between different flight point simulations. The servo system can be programmed with different pressure profiles, force magnitudes, and oscillation frequencies corresponding to various flight conditions, allowing comprehensive validation of multiple flight points without time-consuming mechanical resetup
Solution Approach 2:
The patent employs periodic oscillation of the servo actuator to simulate dynamic aerodynamic loads at different frequencies corresponding to various flight points. By programmatically varying the oscillation frequency and amplitude through fluid pressure control, the system can efficiently test actuator response across multiple flight conditions in a continuous testing sequence rather than requiring separate setup for each condition
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 the quick and accurate simulation of dynamic loads, reducing setup time and allowing for the validation of actuator performance in a manner closer to real-world aircraft conditions, thereby facilitating faster integration into flight systems.
Implementation Method 1
a force actuator configured to generate at least one dynamic load and inserted between the fixed frame and the mobile frame
Implementation Method 2
at least one pressure sensor configured to measure a pressure inside at least one chamber of the force actuator
Implementation Method 3
a controller for controlling the dynamic load generated by the force actuator depending on the pressure measured inside one of the chambers
Data Source
AI summary
A test bench for generating aerodynamic loads on an actuator to be tested includes a force actuator configured to generate at least one dynamic load, the test bench being configured to transmit the dynamic load produced by the force actuator to the actuator to be tested, and a controller for controlling the dynamic load generated by the force actuator depending on a pressure, measured by a pressure sensor, inside one of the chambers of the force actuator.