Multi-propeller tilting wing dynamic test device and method for wing tilting

Abstract

The invention provides a multi-propeller tilting wing dynamic test device for wing tilting. The multi-propeller tilting wing dynamic test device comprises a multi-propeller dynamic test model, a wing dynamic tilting system, an EX1629 data acquisition system and a structural deformation test system, wherein the multi-propeller dynamics test model is composed of one pair of half-expanded wings and three pairs of propellers; the wing dynamic tilting system is composed of a control cabinet and a wing dynamic tilting device, and the wing dynamic tilting device is used for controlling the wing tilt angle, has the capacity of realizing wing constant-speed tilting and triangular wave pulse excitation, and realizes synchronous change of the angles of the wing and the rotor; the EX1629 data acquisition system comprises a data acquisition and vibration monitoring system and is used for measuring a wing profile bending moment load and vibration loads of a nacelle and a wing; the structural deformation testing system is composed of an industrial camera and a high-frequency photography lamp and is used for measuring wing and blade position deformation; meanwhile, the invention further provides a multi-propeller tilting wing dynamics test method for wing tilting.

Description

Technical Field

[0001] The present application belongs to the technical field of helicopter rotor dynamics, and in particular relates to a multi-blade tilt-wing dynamics test device and method for wing tilt. Background Art

[0002] Multi-propeller tilt-wing aircraft combines the vertical take-off and landing capabilities of helicopters with the high-speed cruising capabilities of fixed-wing aircraft, and is one of the important configurations for the electrification, intelligence, high-speed and long-range development of future rotorcraft. The entire aircraft adopts a tilt-wing layout, with typical flight modes such as vertical take-off and landing, tilt-rotation transition, and high-speed forward flight. In particular, the rotation flutter problem during tilt-rotation transition and high-speed forward flight is the most serious dynamic problem of this configuration aircraft.

[0003] Based on the verification needs of aeroelastic response and stability of the aeroelastic analysis method of multi-propeller tilt-wing, the design and verification of multi-propeller tilt-wing model test pieces are carried out, and a multi-propeller tilt-wing dynamics test device considering wing tilt is developed. By integrating the test capabilities and verification needs, typical test wind speeds and wing inclination angles are selected to carry out aeroelastic response and vibration measurements of multi-propeller tilt-wings, verify the correctness of the analysis method, and further improve the research methods of aeroelastic coupling of multi-propeller tilt-wings. Summary of the invention

[0004] Purpose of the invention: To provide a multi-propeller tilt-wing dynamics test device taking wing tilt into consideration, to realize the dynamic attitude conversion function of the multi-propeller wing, to obtain test data under the conditions of wing tilt-wing hovering, forward flight, and tilt transition conversion process, and to further improve the research methods of aeroelastic coupling of multi-propeller tilt-wing.

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

[0006] The multi-propeller dynamics test model consists of one half-span wing and three propellers;

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

[0008] EX1629 data acquisition system, including data acquisition and vibration monitoring systems, used to measure wing section bending moment loads and nacelle and wing vibration loads;

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

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

[0011] Preferably, the device further comprises:

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

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

[0014] A strain gauge, arranged on the half-span wing;

[0015] The vibration sensors are arranged on the half-span wing and the propeller.

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

[0017] In a second aspect, the present application also provides a multi-propeller tilt-wing dynamics test method for wing tilt, the method comprising:

[0018] Measure wing bending moment loads;

[0019] Measure wing nacelle vibration loads;

[0020] Measure wing and blade displacement deformation.

[0021] Preferably, the measuring of the wing bending moment load comprises:

[0022] Install the wing horizontally on the wing dynamic tilting device, and fix the wing dynamic tilting device on the test bench;

[0023] Paste strain gauges on the designated sections of the wing. For the strain gauges in the vertical bending direction of the wing, paste the full bridge on the upper and lower surfaces of the pitch axis position. For the strain gauges in the chord bending direction, paste the full bridge and decouple them.

[0024] After the strain gauge is attached, the wing bending moment load is calibrated. The loading is divided into five levels. The average value of three data is taken for each loading. After recording the results, the linearity and coupling coefficients are analyzed. The calibration is completed when it meets the requirements.

[0025] The voltage signals of each wing bridge circuit that has been calibrated and decoupled are sent to the EX1629 data acquisition system through the test cable and the programmable amplifier. Finally, the signals collected by the EX1629 data acquisition system are monitored and recorded in real time to obtain the wing bending moment load.

[0026] Preferably, the measuring of the vibration load of the wing nacelle comprises:

[0027] A vibration sensor is embedded in each rotor nacelle, and six vibration sensors are pasted on the leading and trailing edges of the specified cross-section positions on the wing upper surface. The vibration signal is transmitted to the EX1629 data acquisition system through the vibration sensor cable via the constant current adapter. Finally, the vibration signal collected by the EX1629 data acquisition system is monitored and recorded in real time on the host computer.

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

[0029] Reflective markers are pasted on the wing tips and blade tips, and industrial cameras and high-frequency photography lights are fixed on the wing roots. The high-frequency photography lights illuminate the wing tips and blade tips horizontally to increase the amount of light entering the industrial camera when collecting pictures. The TTL signal of the frequency-doubling synchronous converter is processed by frequency doubling, and then the industrial camera is triggered to collect an image with reflective markers on the wing and blades in real time at a fixed phase. The camera data is transmitted to the computer in real time to process the image data, and the displacement deformation of the wing and blade is obtained.

[0030] Beneficial technical effects of this application:

[0031] Based on existing test facilities, this application designs a flexible wing with an adjustable tilt angle and a propeller mechanism, wherein the propeller is driven by a motor and the wing is driven to tilt by a dynamic tilt device. The wing structure is designed with reference to fixed-wing aircraft, and 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 actual measured dynamic data of the hovering, forward flight and transient transition states of a multi-propeller tilt-wing aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 A multi-propeller tilt-wing dynamics test device provided in an embodiment of the present application;

[0033] Figure 2 It is a diagram showing the variation of the flapping bending moment of the wing 1200 section with wind speed and wing attack angle provided in an embodiment of the present application;

[0034] Figure 3 It is a diagram of vertical bending displacement law of a 0-90° tilt wing provided in an embodiment of the present application;

[0035] Among them: 1. Dynamic tilt device of the wing; 2. Industrial camera; 3. High-frequency photographic light; 4. Half-spread wing; 5. Strain gauge; 6. Vibration sensor; 7. Reflective marker; 8. Rotor drive motor; 9. Propeller. DETAILED DESCRIPTION

[0036] The present application provides a multi-blade tilt-wing dynamic test device that takes into account wing tilt. Based on existing test facilities, a flexible wing with a propeller mechanism with adjustable tilt angle is designed, wherein the propeller is driven by a motor, and the wing is driven to tilt by a dynamic tilt device. The wing structure is designed with reference to fixed-wing aircraft, and the sensors arranged on the structure or non-contact optical displacement sensors are used to measure the real-time response of the key positions of the rotor and wing, thereby establishing the dynamic measured data of the multi-blade tilt-wing aircraft in hovering, forward flight and transient transition states. Finally, the correlation analysis between theoretical calculation and measured data is carried out, and the theoretical method is fed back and corrected.

[0037] See also Figure 1-Figure 3 In other embodiments of the present application, a multi-propeller tilt-wing dynamics test device is mainly composed of five parts: a test bench, a wing dynamic tilt system, a multi-propeller dynamics test model, an EX1629 data acquisition system, and a structural deformation test system.

[0038] Among them, the test bench provides fixed support for the test models and equipment.

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

[0040] Among them, the multi-propeller dynamics test model consists of one half-span wing, three propellers (one thrust propeller, two lift propellers, including a rotor hub) and three rotor drive motors. The propellers are installed on the wing nacelle through the rotor drive motors, and the wings are installed on the wing dynamic tilt device through the wing root flange.

[0041] Among them, the EX1629 data acquisition system includes data acquisition and vibration monitoring systems. The data acquisition system mainly measures and collects the wing section bending moment load data through strain gauges and measures and collects the vibration load and vibration acceleration data of the nacelle and wing through vibration sensors.

[0042] Among them, the vibration monitoring system monitors the vibration acceleration data of the nacelle and wings through vibration sensors.

[0043] Among them, the structural deformation test system is mainly composed of industrial cameras, high-frequency photographic lights and reflective markers. The industrial cameras and high-frequency photographic lights are installed on the wing root flange, and the reflective markers are pasted on the wing tips and blade tips. The deformation of the wing tips and blade tips is measured by shooting the reflective markers with industrial cameras to reflect the light of the high-frequency photographic lights.

[0044] In other embodiments of the present application, for measuring the wing bending moment load, the wing is horizontally mounted on a wing dynamic tilt device, and the wing dynamic tilt device is fixed on a test bench.

[0045] Strain gauges are pasted on the specified sections of the wing. For the strain gauges in the vertical bending direction of the wing, the full bridge is pasted on the upper and lower surfaces of the pitch axis position. For the strain gauges in the chord bending direction, the full bridge is pasted and decoupled. After the strain gauges are pasted, the wing bending moment load is loaded and calibrated. The loading is divided into five levels. The average value of three data is taken for each loading. After recording the results, the linearity and coupling coefficients are analyzed. The calibration is completed when it meets the requirements (coupling coefficient <5%). The voltage signals of each bridge circuit of the wing that has been calibrated and decoupled are entered into the EX1629 data acquisition system through the test cable and the programmable amplifier. Finally, the signals collected 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 the present application, the vibration load of the wing nacelle is measured by pre-embedded a vibration sensor in each rotor nacelle, and six vibration sensors are attached to the leading and trailing edges of specified cross-sectional positions on the upper surface of the wing. The vibration signal is transmitted through the vibration sensor cable via the constant current adapter to the EX1629 data acquisition system, and finally the vibration signal collected by the EX1629 data acquisition system is monitored and recorded in real time on the host computer.

[0047] In other embodiments of the present application, the displacement and deformation of the wing and blade are measured, reflective markers are pasted on the wingtips and blade tips, an industrial camera and a high-frequency photographic light are fixed at the wing roots, and the high-frequency photographic light illuminates the wingtips and blade tips horizontally to increase the amount of light entering the industrial camera when capturing images.

[0048] Furthermore, by multiplying the frequency of the TTL signal of the frequency multiplication synchronous converter, the industrial camera is triggered to collect an image with reflective markers on the wing and blade in real time at a fixed phase, and the industrial camera data is transmitted to the computer in real time to process the image data, thereby obtaining the displacement deformation of the wing and blade.

[0049] In other embodiments of the present application, in a multi-propeller tilt-wing dynamics test, a multi-propeller dynamics test model is installed on a test bench through a wing dynamic tilt device, and initial readings are collected by an EX1629 data acquisition system and a structural deformation test system; the wind tunnel wind speed and the rotor speed are alternately adjusted to the test wind speed and the test speed, and the wing dynamic tilt device adjusts the wing angle of attack to the test tilt angle. If it is a pulse excitation or a tilt transition state, the wing dynamic tilt 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 test system respectively collect the wing section bending moment, nacelle / wing vibration load, and wing and blade displacement deformation, ensuring at least 10 seconds of valid data; after all states of the current wind speed are completed, the wing angle of attack returns to zero, the rotor speed returns to zero, and the wind speed returns to zero.

[0051] It should be noted that the present application provides a multi-propeller tilt-wing dynamics test device considering wing tilt, such as Figure 1 According to the laws and conclusions established in the theoretical research on aeroelastic coupling of multi-propeller tilt-wings, and based on the needs of dynamic analysis and verification, we carried out test scheme research and formed test procedures and measurement methods. Subsequently, we carried out dynamic tests on multi-propeller tilt-wings to collect data such as the aeroelastic response, displacement, and vibration load of the multi-propeller system under different flight conditions.

[0052] Take the wing 1200 section as an example. Figure 2 It can be seen that within the wing angle of attack of 20 degrees, the wing flapping bending moment increases linearly with the angle of attack, and the greater the wind speed, the more obvious the increase in the flapping bending moment; the flapping bending moment under different wind speeds has the same trend with the angle of attack.

[0053] The multi-propeller transient tilt transition test was carried out to measure the vertical bending displacement deformation of the wing tip during the tilt transition process of the multi-propeller system at different wind speeds. Figure 3 It can be seen that the three wing tip flapping displacements under the tilt transition are almost the same, and the repeatability is good.

[0054] Through correlation analysis with theoretical calculations, the calculation results are consistent with the experimental results, which verifies the established aeroelastic dynamics analysis method of multi-propeller tilt-wing, further improves the research means of aeroelastic coupling of multi-propeller tilt-wing, masters the complex aeroelastic-inertial coupling mechanism between the multi-propeller nacelle and wing of the multi-propeller tilt-wing coupling system, finds out the flutter instability boundary and formation mechanism, and forms a set of mature multi-propeller tilt-wing dynamics test equipment and experimental testing methods.

Claims

1. A multi-propeller tilt-wing dynamics test device for wing tilt, characterized in that: The device includes: a multi-propeller dynamics test model, a wing dynamic tilting system, an EX1629 data acquisition system, and a structural deformation test system; The multi-propeller dynamics test model consists of one half-span wing and three propellers; The wing dynamic tilting system is composed of a control cabinet and a wing dynamic tilting device. The wing dynamic tilting device is used to control the wing tilt angle, and has the ability to realize uniform wing tilting and triangular wave pulse excitation, so as to realize synchronous changes in the wing and rotor angles. EX1629 data acquisition system, including data acquisition and vibration monitoring systems, used to measure wing section bending moment loads and nacelle and wing vibration loads; The structural deformation test system, consisting of an industrial camera and a high-frequency photographic light, is used to measure the positional deformation of wings and blades.

2. The device according to claim 1, characterized in that The propeller comprises one pair of thrust propellers and two pairs of lift propellers.

3. The device according to claim 1, characterized in that The device also includes: The test bench is used to provide fixed support for the wing dynamic tilting device, the multi-propeller dynamics test model and the structural deformation test system during the test.

4. The device according to claim 3, characterized in that The EX1629 data acquisition system includes: A strain gauge, arranged on the half-span wing; The vibration sensors are arranged on the half-span wing and the propeller.

5. The device according to claim 4, characterized in that The control cabinet is connected to the wing dynamic tilting device, the wing dynamic tilting device is arranged on the test bench, and the camera and high-frequency photography light are installed on the flange of the half-span wing.

6. A method for dynamic testing of a multi-propeller tilt-wing with wing tilt, characterized in that: The method comprises: Measure wing bending moment loads; Measure wing nacelle vibration loads; Measure wing and blade displacement deformation.

7. The method according to claim 6, characterized in that The measuring of wing bending moment load comprises: Install the wing horizontally on the wing dynamic tilting device, and fix the wing dynamic tilting device on the test bench; Paste strain gauges on the designated sections of the wing. For the strain gauges in the vertical bending direction of the wing, paste the full bridge on the upper and lower surfaces of the pitch axis position. For the strain gauges in the chord bending direction, paste the full bridge and decouple them. After the strain gauge is attached, the wing bending moment load is calibrated. The loading is divided into five levels. The average value of three data is taken for each loading. After recording the results, the linearity and coupling coefficients are analyzed. The calibration is completed when it meets the requirements. The voltage signals of each wing bridge circuit that has been calibrated and decoupled are sent to the EX1629 data acquisition system through the test cable and the programmable amplifier. Finally, the signals collected by the EX1629 data acquisition system are monitored and recorded in real time to obtain the wing bending moment load.

8. The method according to claim 6, characterized in that The method of measuring the vibration load of the wing nacelle comprises: A vibration sensor is embedded in each rotor nacelle, and six vibration sensors are pasted on the leading and trailing edges of the specified cross-section positions on the wing upper surface. The vibration signal is transmitted to the EX1629 data acquisition system through the vibration sensor cable via the constant current adapter. Finally, the vibration signal collected by the EX1629 data acquisition system is monitored and recorded in real time on the host computer.

9. The method according to claim 6, characterized in that The measuring of wing and blade displacement deformation comprises: Reflective markers are pasted on the wing tips and blade tips, and industrial cameras and high-frequency photography lights are fixed on the wing roots. The high-frequency photography lights illuminate the wing tips and blade tips horizontally to increase the amount of light entering the industrial camera when collecting pictures. The TTL signal of the frequency-doubling synchronous converter is processed by frequency doubling, and then the industrial camera is triggered to collect an image with reflective markers on the wing and blades in real time at a fixed phase. The camera data is transmitted to the computer in real time to process the image data, and the displacement deformation of the wing and blade is obtained.

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