Application Cases

Experiment Name: Design and Experimental Verification of Wing Deformation Control System

Test Purpose: The design of open-loop and closed-loop control systems for variable camber wings considering the hysteresis and creep characteristics compensation of MFC actuators, and ground experimental research on wing camber deformation. The actual wing camber deformation situation is examined through experimental means to verify the feasibility and effectiveness of the proposed variable camber wing design and control methods.

Testing Equipment: Voltage amplifier, piezoelectric fiber actuator, laser displacement sensor, data acquisition card, etc.

Figure 1: Block Diagram of the Experimental System

Experiment Process:

Static deformation tests were conducted on the designed deformable wing. In the experiment, the MFC voltage loading range was set to [0, 1500] V, and a "step" form of voltage loading signal as shown in Figure 2 was selected. The control voltage was applied to the MFC in increments of 100 V every 60 s until the entire voltage loading range was covered. During the experiment, the displacement changes at the measurement points of the wing trailing edge were collected in real time using a laser displacement sensor to perceive the control effect of the MFC actuator on the wing camber deformation.

Figure 2: Loading Voltage

Experimental Results:

Figure 3: Displacement Changes at the Wing Trailing Edge

Figure 3 shows the variation curve of the wing trailing edge deformation under the driving of the loading voltage shown in Figure 2. The experimental results indicate that as the control voltage increases, the wing deformation increases approximately linearly. Within the piezoelectric driving range, the maximum effective deformation at the wing tip can reach 7.8 mm (corresponding to a loading voltage of 1500 V). The experimental results also show that within each stable voltage loading range, the wing trailing edge deformation exhibits an "upward drift" trend, which is due to the hysteresis and creep characteristics of the MFC actuator. The above experimental results demonstrate that the designed deformable wing can achieve significant driving deformation under the control of the MFC, but the system control effect is also disturbed by the hysteresis and creep nonlinear characteristics of the MFC actuator.

Figure 4: Comparison of Experimental and Simulation Results

Figure 4 is a comparison of the experimental results and the computational results obtained from finite element simulation in this chapter. Comparing the two figures reveals that the variation trends of loading voltage and deformation obtained by the two methods are basically the same, but the wing deformation obtained by simulation calculation is slightly larger than that measured in the experiment. This is due to the fact that the influence of the MFC actuator and epoxy resin glue on the structural performance was not considered in the finite element modeling process, and the hysteresis and creep effects of the MFC actuator itself were not compensated in the experiment in this section.

Voltage Amplifier Recommendation: ATA-2161

Figure: Specification Parameters of the ATA-2161 High-Voltage Amplifier

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