A multi-bladed tilting wing dynamics test apparatus and method

Abstract

The application provides a multi-propeller wing dynamics test device with wing tilting, comprising a multi-propeller dynamics test model, a wing dynamic tilting system, an EX1629 data acquisition system and a structure deformation test system; wherein the multi-propeller dynamics test model comprises half-span wings and three pairs of propellers; the wing dynamic tilting system comprises a control cabinet and a wing dynamic tilting device, the wing dynamic tilting device is used for controlling the wing tilting angle, has the ability of realizing uniform-speed tilting of the wing and triangular wave pulse excitation, and realizes synchronous change of the wing and the rotor angle; the EX1629 data acquisition system comprises a data acquisition and vibration monitoring system and is used for measuring the bending moment load of the wing section, the vibration load of the nacelle and the wing; the structure deformation test system comprises an industrial camera and a high-frequency photographic lamp and is used for measuring the wing and propeller position deformation; meanwhile, the application also provides a multi-propeller wing dynamics test method with wing tilting.

Description

Technical Field

[0001] This application belongs to the field of helicopter rotor dynamics technology, and particularly relates to a multi-rotor tilting wing dynamics test device and method. Background Technology

[0002] Multi-rotor tiltrotor aircraft combine the vertical takeoff and landing capabilities of helicopters with the high-speed cruise capabilities of fixed-wing aircraft, representing a crucial configuration for the future development of electrified, intelligent, high-speed, and long-range rotorcraft. The entire aircraft employs a tiltrotor wing layout, featuring typical flight modes such as vertical takeoff and landing, tilt transition, and high-speed forward flight. Notably, the flutter during tilt transition and high-speed forward flight are the most severe dynamic challenges for this type of aircraft.

[0003] Based on the verification requirements of aeroelastic response and stability of multi-rotor tilt-wing aeroelastic analysis method, this study designs and verifies a multi-rotor tilt-wing model test piece, develops a dynamic test device for multi-rotor tilt-wing considering wing tilt, and comprehensively considers test capabilities and verification requirements. Typical test wind speeds and wing tilt angles are selected to conduct aeroelastic response and vibration measurements of the multi-rotor tilt-wing, verify the correctness of the analysis method, and further improve the aeroelastic coupling research methods for multi-rotor tilt-wing. Summary of the Invention

[0004] Purpose of the invention: To provide a dynamic test device for multi-rotor tilt-wing aircraft that considers wing tilting, realizes the dynamic attitude conversion function of multi-rotor wing, and obtains test data in states such as wing tilting hovering, forward flight, and tilting transition process, so as to further improve the aeroelastic coupling research method of multi-rotor tilt-wing aircraft.

[0005] In a first aspect, this application provides a multi-rotor tilting wing dynamics test device, the device comprising: a multi-rotor dynamics test model, a wing dynamic tilting system, an EX1629 data acquisition system, and a structural deformation test system;

[0006] The multi-propeller dynamic test model consists of one half-wing and three propellers.

[0007] The wing dynamic tilt system consists of a control cabinet and a wing dynamic tilt device. The wing dynamic tilt device is used to control the wing tilt angle and has the ability to achieve uniform wing tilt and triangular wave pulse excitation, so as to realize the synchronous change of wing and rotor angles.

[0008] The EX1629 data acquisition system, including a data acquisition and vibration monitoring system, is used to measure the bending moment load on the airfoil profile and the vibration load on the nacelle and wing.

[0009] The structural deformation testing system, consisting of an industrial camera and a high-frequency photographic light, is used to measure the deformation of the wing and blades.

[0010] Preferably, the propeller includes one thrust propeller and two lift propellers.

[0011] Preferably, the device further includes:

[0012] The test bench is used to provide fixed support for the wing dynamic tilting device, the multi-rotor dynamic test model, and the structural deformation test system during the test.

[0013] Preferably, the EX1629 data acquisition system includes:

[0014] Strain gauges are mounted on the semi-extension wing;

[0015] Vibration sensors are installed on the half-wing and propeller.

[0016] Preferably, the control cabinet is connected to the wing dynamic tilting device, the wing dynamic tilting device is set on the test bench, and the camera and high-frequency photography light are mounted on the flange of the half-wing.

[0017] Secondly, this application also provides a dynamic test method for a multi-rotor tiltrotor wing, the method comprising:

[0018] Measure the bending moment load on the wing;

[0019] Measure the vibration load of the wing nacelle;

[0020] Measure the displacement and deformation of the wing and blades.

[0021] Preferably, the method for measuring wing bending moment load includes:

[0022] The wing is horizontally mounted on the wing dynamic tilting device, and the wing dynamic tilting device is fixed on the test bench;

[0023] Strain gauges are attached to designated sections of the wing. For strain gauges in the vertical bending direction of the wing, they are attached to the upper and lower surfaces of the variable pitch axis as a full bridge. For strain gauges in the chordal bending direction, they are attached as a full bridge and decoupled.

[0024] After attaching the strain gauges, the bending moment load on the wing was calibrated by loading it in five stages. The average value of three data points was taken for each loading. The results were recorded and the linearity and coupling coefficients were analyzed. The calibration was completed after the requirements were met.

[0025] The voltage signals of each bridge circuit of the calibrated and decoupled wing are fed into the EX1629 data acquisition system through test cables and a programmable amplifier. Finally, the signals acquired by the EX1629 data acquisition system are monitored and recorded in real time to obtain the wing bending moment load.

[0026] Preferably, the method for measuring the vibration load of the wing nacelle includes:

[0027] A vibration sensor is pre-embedded in each rotor nacelle, and six vibration sensors are attached to the leading and trailing edges of a designated section on the upper surface of the wing. The vibration signals are transmitted through the vibration sensor cables to the EX1629 data acquisition system via a constant current adapter. Finally, the vibration signals acquired by the EX1629 data acquisition system are monitored and recorded in real time on the host computer.

[0028] Preferably, the measurement of wing and blade displacement deformation includes:

[0029] Reflective markers are affixed to the wingtips and propeller tips. An industrial camera and a high-frequency photographic light are fixed at the wing root. The high-frequency photographic light illuminates the wingtips and propeller tips horizontally to increase the amount of light entering the industrial camera when capturing images. The TTL signal is frequency-doubled by a frequency-doubled synchronous converter, which then triggers the industrial camera to capture an image with the reflective markers on the wings and propellers in real time at a fixed phase. The camera data is transmitted to a computer in real time for image processing, resulting in the displacement and deformation of the wings and propellers.

[0030] The beneficial technical effects of this application are as follows:

[0031] Based on existing experimental facilities, this application designs a flexible wing with an adjustable tilt angle and a propeller mechanism. The propeller is driven by an electric motor, and the wing is tilted by a dynamic tilting device. The wing structure is designed with reference to fixed-wing aircraft. Sensors arranged on the structure or non-contact optical displacement sensors are used to measure the real-time response of key positions of the rotor and wing, thereby establishing dynamic measurement data of the hovering, forward flight and transient transition states of the multi-propeller tilt wing aircraft. Attached Figure Description

[0032] Figure 1 This application provides a multi-rotor tilting wing dynamics test device.

[0033] Figure 2 This is a diagram showing the variation of flapping moment of the wing at a 1200 section with wind speed and wing angle of attack, provided in an embodiment of this application.

[0034] Figure 3 This is a diagram illustrating the vertical bending displacement of a tilting wing from 0 to 90°, provided in an embodiment of this application.

[0035] The components include: 1. Wing dynamic tilting device; 2. Industrial camera; 3. High-frequency photography light; 4. Half-wing; 5. Strain gauge; 6. Vibration sensor; 7. Reflective marker; 8. Rotor drive motor; 9. Propeller. Detailed Implementation

[0036] This application provides a multi-rotor tilt-wing dynamics test device considering wing tilt. Based on existing test facilities, a flexible wing with an adjustable tilt angle and a propeller mechanism is designed. The propeller is driven by an electric motor, and the wing tilts via a dynamic tilting device. The wing structure is designed with reference to fixed-wing aircraft. Sensors arranged on the structure or non-contact optical displacement sensors are used to measure the real-time response of key positions of the rotor and wing, thereby establishing measured dynamic data for hovering, forward flight, and transient transition states of the multi-rotor tilt-wing aircraft. Finally, correlation analysis between theoretical calculations and measured data is performed to provide feedback and correct the theoretical methods.

[0037] Please see Figures 1-3 In other embodiments of this application, the multi-rotor tilting wing dynamics test device mainly consists of five parts: a test bench, a wing dynamic tilting system, a multi-rotor dynamics test model, an EX1629 data acquisition system, and a structural deformation test system.

[0038] The test bench provides fixed support for the test model and equipment.

[0039] The wing dynamic tilt system mainly consists of a control cabinet and a wing dynamic tilt device. The control cabinet can control the wing dynamic tilt device to change the wing tilt angle. The wing dynamic tilt device consists of a servo motor, a first-stage planetary reducer, a second-stage planetary reducer, and a tilt sensor. It has the ability to achieve uniform wing tilt and triangular wave pulse excitation, and realize the synchronous change of wing and rotor angles. The wing dynamic tilt device is directly installed on the test bench.

[0040] The multi-propeller dynamic test model consists of one half-wing, three propellers (one thrust propeller and two lift propellers, including the rotor hub) and three rotor drive motors. The propellers are mounted on the wing nacelles via the rotor drive motors, and the wings are mounted on the wing dynamic tilting device via the wing root flange.

[0041] The EX1629 data acquisition system includes a data acquisition and vibration monitoring system. The data acquisition system mainly measures and collects the bending moment load data of the airfoil profile through strain gauges and measures and collects the vibration load and vibration acceleration data of the nacelle and wing through vibration sensors.

[0042] The vibration monitoring system monitors the vibration acceleration data of the nacelle and wing using vibration sensors.

[0043] The structural deformation testing system mainly consists of an industrial camera, a high-frequency photographic light, and a reflective marker. The industrial camera and the high-frequency photographic light are mounted on the wing root flange, and the reflective marker is attached to the wingtip and blade tip. The deformation of the wingtip and blade tip is measured by photographing the light reflected from the high-frequency photographic light by the reflective marker using the industrial camera.

[0044] In other embodiments of this application, the wing bending moment load is measured by horizontally mounting the wing on a wing dynamic tilting device and fixing the wing dynamic tilting device on a test bench.

[0045] Strain gauges are attached to designated sections of the wing. For strain gauges in the vertical bending direction, they are attached to the upper and lower surfaces of the variable pitch axis as a full bridge. For strain gauges in the chordal bending direction, they are attached as a full bridge and decoupled. After attaching the strain gauges, the wing bending moment load is calibrated by loading in five stages. The average value of three data points is taken for each loading. The results are recorded and the linearity and coupling coefficient are analyzed. The calibration is completed when the requirements are met (coupling coefficient <5%). The voltage signals of each bridge circuit of the calibrated and decoupled wing are sent to the EX1629 data acquisition system through test cables and a programmable amplifier. Finally, the signals acquired by the EX1629 data acquisition system are monitored and recorded in real time to obtain the wing bending moment load.

[0046] In other embodiments of this application, vibration load measurement of the wing nacelle involves pre-embedding a vibration sensor in each rotor nacelle and attaching six vibration sensors to the leading and trailing edges of a designated section on the upper surface of the wing. The vibration signals are transmitted via vibration sensor cables to the EX1629 data acquisition system through a constant current adapter. Finally, the vibration signals acquired by the EX1629 data acquisition system are monitored and recorded in real time on the host computer.

[0047] In other embodiments of this application, wing and blade displacement deformation measurement involves attaching reflective markers to the wingtips and blade tips, and fixing an industrial camera and a high-frequency photographic light at the wing root. The high-frequency photographic light illuminates the wingtips and blade tips horizontally to increase the amount of light entering the industrial camera when acquiring images.

[0048] Furthermore, by performing frequency multiplication on the TTL signal of the frequency multiplier synchronous converter, an industrial camera is triggered to capture an image with reflective markers on the wings and blades in real time at a fixed phase. The industrial camera data is then transmitted to a computer in real time for image data processing to obtain the displacement and deformation of the wings and blades.

[0049] In other embodiments of this application, the multi-rotor tilt-wing dynamics test involves mounting the multi-rotor dynamics test model on a test bench using a wing dynamic tilting device. The EX1629 data acquisition system and the structural deformation testing system collect initial readings. The wind tunnel wind speed and rotor speed are alternately adjusted to the test wind speed and test speed. The wing dynamic tilting device adjusts the wing angle of attack to the test tilt angle. If it is a pulse excitation or tilt transition state, the wing dynamic tilting device changes the wing angle of attack according to the set wing angle of attack time domain history.

[0050] During the test, the EX1629 data acquisition system and structural deformation testing system collected the wing profile bending moment, nacelle / wing vibration load, and wing and blade displacement deformation, respectively, ensuring at least 10 seconds of valid data; after all the current wind speed conditions were completed, the wing angle of attack returned to zero, the rotor speed returned to zero, and the wind speed returned to zero.

[0051] It should be noted that the multi-rotor tilt-wing dynamics test device considering wing tilting provided in this application, such as... Figure 1 Based on the established laws and conclusions of the aeroelastic coupling theory of multi-rotor tiltrotor aircraft, and the need for verification through dynamic analysis, experimental schemes were developed, and experimental procedures and measurement methods were formed. Subsequently, dynamic experiments on multi-rotor tiltrotor aircraft were conducted, and data such as aeroelastic response, displacement, and vibration load of the multi-rotor system were collected under different flight conditions.

[0052] Taking the 1200 section of the wing as an example, from Figure 2 As can be seen, within an angle of attack of 20 degrees, the flapping moment of the wing increases linearly with the angle of attack, and the increase in flapping moment is more significant with higher wind speeds; the trend of flapping moment with angle of attack is consistent under different wind speeds.

[0053] A multi-propeller transient tilt transition test was conducted, measuring the vertical bending displacement deformation of the wingtips during the tilt transition process of the multi-propeller system under different wind speeds. Figure 3 It can be seen that the wingtip flapping displacements during the three tilt transitions are almost identical, indicating good repeatability.

[0054] Correlation analysis with theoretical calculations showed that the calculation results were in good agreement with the experimental results, verifying the established aeroelastic dynamics analysis method for multi-rotor tiltrotor aircraft. This further improved the aeroelastic coupling research methods for multi-rotor tiltrotor aircraft, helped to understand the complex aeroelastic inertial coupling mechanism between the multi-rotor nacelle wings in the multi-rotor tiltrotor aircraft coupling system, clarified the flutter instability boundary and formation mechanism, and formed a mature multi-rotor tiltrotor aircraft dynamics test device and test method.

Claims

1. A dynamic testing method for a multi-rotor tilt-wing, characterized in that, The method includes: Measure the bending moment load on the wing; Measure the vibration load of the wing nacelle; Measure the displacement and deformation of the wing and blades; The method for measuring wing bending moment load includes: The wing is horizontally mounted on the wing dynamic tilting device, and the wing dynamic tilting device is fixed on the test bench; Strain gauges are attached to designated sections of the wing. For strain gauges in the vertical bending direction of the wing, they are attached to the upper and lower surfaces of the variable pitch axis as a full bridge. For strain gauges in the chordal bending direction, they are attached as a full bridge and decoupled. After attaching the strain gauges, the bending moment load on the wing was calibrated by loading it in five stages. The average value of three data points was taken for each loading. The results were recorded and the linearity and coupling coefficients were analyzed. The calibration was completed after the requirements were met. The voltage signals of each bridge circuit of the calibrated and decoupled wing are sent to the EX1629 data acquisition system through test cables and programmable amplifiers. Finally, the signals acquired by the EX1629 data acquisition system are monitored and recorded in real time to obtain the wing bending moment load. The measured vibration load of the wing nacelle includes: A vibration sensor is pre-embedded in each rotor nacelle, and six vibration sensors are attached to the leading and trailing edges of a designated section on the upper surface of the wing. The vibration signals are transmitted through the vibration sensor cables to the EX1629 data acquisition system via a constant current adapter. Finally, the vibration signals acquired by the EX1629 data acquisition system are monitored and recorded in real time on the host computer. The measurement of wing and blade displacement deformation includes: Reflective markers are affixed to the wingtips and propeller tips. An industrial camera and a high-frequency photographic light are fixed at the wing root. The high-frequency photographic light illuminates the wingtips and propeller tips horizontally to increase the amount of light entering the industrial camera when capturing images. The TTL signal is multiplied by a frequency multiplier converter, which then triggers the industrial camera to capture an image with the reflective markers on the wing and propeller in real time at a fixed phase. The camera data is transmitted to a computer in real time for image processing, and the displacement and deformation of the wing and propeller are obtained.

2. A dynamic test device for a multi-rotor tilting wing, characterized in that, The device is used to implement the method as described in claim 1, and the device includes: a multi-rotor dynamic test model, a wing dynamic tilting system, an EX1629 data acquisition system, and a structural deformation test system; The multi-propeller dynamic test model consists of one half-wing and three propellers. The wing dynamic tilt system consists of a control cabinet and a wing dynamic tilt device. The wing dynamic tilt device is used to control the wing tilt angle and has the ability to achieve uniform wing tilt and triangular wave pulse excitation, so as to realize the synchronous change of wing and rotor angles. The EX1629 data acquisition system, including a data acquisition and vibration monitoring system, is used to measure the bending moment load on the airfoil profile and the vibration load on the nacelle and wing. The structural deformation testing system, consisting of an industrial camera and a high-frequency photographic light, is used to measure the deformation of the wing and blades.

3. The apparatus according to claim 2, characterized in that, The propeller includes one thrust propeller and two lift propellers.

4. The apparatus according to claim 3, characterized in that, The device further includes: The test bench is used to provide fixed support for the wing dynamic tilting device, the multi-rotor dynamic test model, and the structural deformation test system during the test.

5. The apparatus according to claim 4, characterized in that, The EX1629 data acquisition system includes: Strain gauges are mounted on the semi-extension wing; Vibration sensors are installed on the half-wing and propeller.

6. The apparatus according to claim 5, characterized in that, The control cabinet is connected to the wing dynamic tilting device, which is set on the test bench. The camera and high-frequency photography light are mounted on the flange of the half-wing.

Images