Fish bone imitating concept and zero poisson ratio lattice structure-based driving torque-rotation angle curve measurement test method for wing variable camber structure

Abstract

The invention provides a wing variable camber structure driving torque-rotation angle curve measurement test method based on a fishbone imitation concept and a zero Poisson ratio lattice structure, and the method comprises the steps: firstly calibrating a torque-current relation of a driving steering engine, and then measuring a current-rotation angle relation in a deformation process of the steering engine driving wing variable camber structure; and finally, a torque-rotation angle relation curve of the steering engine in the process of driving the variable-camber structure of the wing to deform is obtained through an isoamperometric method. Core data support is provided for driving mechanism optimization design, aerodynamic efficiency improvement and full-life-cycle reliability verification of self-adaptive wings, and technical development of intelligent variant aircrafts can be promoted.

Description

Technical Field

[0001] The present invention provides a method for measuring the driving torque-rotation angle curve of a variable camber wing structure based on the concept of fishbone imitation and zero Poisson's ratio lattice structure, belonging to the field of aviation. Background Technique

[0002] As the core component of a new generation of adaptive wings, the driving system torque-rotation angle characteristics of the variable camber wing structure directly affect the aerodynamic shape adjustment accuracy and actuator selection. The present invention proposes a method for measuring the driving torque-rotation angle curve of a variable camber wing structure based on the concept of fishbone imitation and zero Poisson's ratio lattice structure. First, the torque-current relationship of the driving servo is calibrated, then the current-rotation angle relationship during the deformation of the servo-driven variable camber wing structure is measured, and finally, the torque-rotation angle relationship curve of the servo during the deformation of the variable camber wing structure is obtained by the equal current method. The present invention provides core data support for the optimal design of the driving mechanism of adaptive wings, the improvement of aerodynamic efficiency, and the verification of the reliability of the entire life cycle, and helps to promote the development of intelligent variable aircraft technology. Summary of the Invention

[0003] The present invention provides a method for measuring the driving torque-rotation angle curve of a variable camber wing structure based on the concept of fishbone imitation and zero Poisson's ratio lattice structure. This method has the advantages of simple process and high precision, and its technical solution is as follows:

[0004] The test method of the present invention is divided into the following 4 steps. Figure 1 It is a schematic diagram of the overall variable camber wing structure for testing. Figure 2 The schematic diagram of the test method principle is given.

[0005] Step 1: Circuit connection. The positive and negative poles of two driving servos are connected to the positive and negative poles of a regulated DC power supply. The signal lines of the two driving servos and the negative pole of the regulated power supply are connected to the receiver. The positive and negative poles of the RC lithium battery are connected to the positive and negative poles of the input end of the electronic speed controller, and the positive and negative poles of the output end of the electronic speed controller are connected to the receiver. The remote control is paired with the receiver so that the receiver can receive the radio signal emitted by the remote control.

[0006] Step 2: Relationship between the current of the driving servo and the servo rotation angle. Slowly move the joystick of the remote control so that the driving servo can rotate evenly, record the current readings when the servo rotates at different angles, and divide the recorded current by 2 to obtain the current of a single servo. In this way, the relationship between the current of the driving servo and the servo rotation angle during the downward deflection and upward deflection processes is obtained.

[0007] Step 3: Relationship between the driving servo torque and the current. The digital display torque wrench is connected to the servo through a connecting piece, and the handles of the driving servo and the torque wrench are fixed. Slowly move the joystick of the remote control so that the servo rotates evenly, and record the readings of the torque wrench and the current values during this process.

[0008] Step 4: Relationship between the driving servo torque and the rotation angle. By integrating the data obtained in Step 2 and Step 3 through the equal current method, the torque corresponding to different rotation angles of the driving servo can be obtained during the deflection of the wing variable camber structure driven by the driving servo. Description of the Drawings

[0009] Figure 1 It is a schematic diagram of the overall wing variable camber structure based on the fishbone-like concept and the zero Poisson's ratio lattice structure.

[0010] Figure 2 It is a schematic diagram of the principle of the test method. Detailed Embodiments

[0011] The present invention provides a test method for measuring the driving torque-rotation angle curve of a wing variable camber structure based on the fishbone-like concept and the zero Poisson's ratio lattice structure. This method has the advantages of simple process and high precision. The technical solution is as follows:

[0012] The test method of the present invention is divided into the following 4 steps. Figure 1 It is a schematic diagram of the overall wing variable camber structure for testing, Figure 2 and a schematic diagram of the principle of the test method is given.

[0013] Step 1: Circuit connection. The positive and negative poles of two driving servos are connected to the positive and negative poles of a regulated DC power supply. The signal lines of the two driving servos and the negative pole of the regulated power supply are connected to the receiver. The positive and negative poles of the RC model lithium battery are connected to the positive and negative poles of the input end of the electronic speed controller, and the positive and negative poles of the output end of the electronic speed controller are connected to the receiver. The remote control is frequency-matched with the receiver so that the receiver can receive the radio signal transmitted by the remote control.

[0014] Step 2: Relationship between the current of the driving servo and the rotation angle of the servo. Slowly move the lever of the remote control to make the driving servo rotate at a constant speed, record the current readings when the servo rotates at different angles, and divide the recorded current by 2 to obtain the current of a single servo. In this way, the relationship between the current of the driving servo and the rotation angle of the servo during the downward and upward deflection processes is obtained.

[0015] Step 3: Relationship between the driving servo torque and the current. The digital display torque wrench is connected to the servo through a connecting piece, and the handles of the driving servo and the torque wrench are fixed. Slowly move the lever of the remote control to make the servo rotate at a constant speed, and record the readings of the torque wrench and the current values during this process.

[0016] Step 4: Relationship between the driving servo torque and the rotation angle. By integrating the data obtained in Step 2 and Step 3 through the equal current method, the torque corresponding to different rotation angles of the driving servo can be obtained during the deflection of the wing variable camber structure driven by the driving servo.

Claims

1. A test method for measuring the driving torque-angle curve of a wing variable camber structure based on the fishbone concept and a zero Poisson's ratio lattice structure, characterized by: The test method of the present invention is divided into the following 4 steps: Step 1: Connect the circuit: Connect the positive and negative terminals of the two servos to the positive and negative terminals of the DC power supply. Connect the signal lines of the two servos and the negative terminal of the power supply to the receiver. Connect the positive and negative terminals of the lithium battery of the model aircraft to the positive and negative terminals of the ESC input terminal, and the positive and negative terminals of the ESC output terminal to the receiver. Bind the remote control to the receiver so that the receiver can receive the radio signal transmitted by the remote control. Step 2: The relationship between the current driving the servo and the servo angle. Move the remote control's lever at a constant speed to make the servo rotate at a constant speed. Record the current readings at different servo rotation angles. Divide the recorded current by 2 to get the current of a single servo. This will give the relationship between the current driving the servo and the servo angle during both downward and upward deflection. Step 3: The relationship between the driving torque and current of the servo; Connect the digital torque wrench to the servo through a connector, and fix the handles of the servo and torque wrench. Move the remote controller's lever at a constant speed to make the servo rotate at a constant speed. Record the torque wrench reading and current value during this process. Step 4: The relationship between the driving torque and the angle of rotation of the servo; By integrating the data obtained in steps 2 and 3 using the equal current method, we can obtain the torque corresponding to different rotation angles of the driving servo during the deflection of the wing variable camber structure.

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