A vibration test system for identifying a tilting rotor blade dynamics parameter

Abstract

A kind of exciting test system for identifying the dynamics parameter of tilting rotor blade belongs to the technical field of blade dynamics test, and the present application is to solve the problems existing in prior art.The present application includes rotor assembly and tilting assembly, the rotor assembly includes six-component balance and reduction gearbox, the six-component balance is connected with the reduction gearbox, bearing seat is arranged on the six-component balance, the rotor shaft is rotatably connected with the bearing seat, the upper end of the rotor shaft is connected with the hub, the driving motor drives the rotor shaft to rotate through gear transmission, a plurality of hydraulic exciting cylinders are arranged on the six-component balance, the total pitch angle of the blade is adjusted by the automatic tilting device, and the reduction gearbox is hinged with the tilting assembly.The present application can realize exciting test of helicopter, fixed wing and tilting transition flight mode, support flexible adjustment of exciting position, amplitude and frequency, accurately match the different modal resonance requirements of blade, greatly reduce the interference of additional mass and stiffness on test, and improve the authenticity of data.

Description

Technical Field

[0001] This invention belongs to the field of blade dynamics testing technology, and particularly relates to a vibration test system for identifying the dynamic parameters of tilt rotor blades. Background Technology

[0002] As a novel type of aircraft combining the high speed and long range of fixed-wing aircraft with the short takeoff / vertical landing (STOVL) capabilities of tiltrotor aircraft, accurate characterization of its dynamic characteristics is a core prerequisite for ensuring flight stability and optimizing controllability design. Especially during the transition between helicopter and fixed-wing modes, the rotor blades must withstand complex aerodynamic loads, inertial loads, and aeroelastic coupling effects. Their natural frequency, damping ratio, and other dynamic parameters directly affect flight safety and maneuverability. Dynamic parameter identification, as the core means of obtaining these key characteristics, requires precise excitation tests to stimulate the blade vibration response, thereby achieving parameter inversion and providing data support for dynamic modeling and structural optimization. However, existing tiltrotor blade excitation testing technologies still have many problems that urgently need to be solved: First, when the blade is rotating, traditional methods such as hammering and hoisting exciters are difficult to achieve effective excitation and are prone to introducing additional mass interference, resulting in distorted vibration response signals and an inability to accurately capture the dynamic characteristics under rotating conditions; Second, tiltrotor aircraft have multiple flight mode switching characteristics, and existing test systems are mostly designed for a single mode, making it difficult to adapt to the excitation requirements of varying operating conditions within the 0~90° tilt angle range, and unable to fully cover the parameter change patterns during mode transitions; Third, in complex test environments such as wind tunnels, conventional excitation devices are easily affected by airflow interference, and sensor placement and signal transmission are easily limited by space, resulting in insufficient accuracy of frequency response data acquisition and difficulty in meeting the parameter identification requirements under aeroelastic coupling scenarios; Fourth, the excitation frequency range and load amplitude adjustment flexibility of existing test systems are limited, making it impossible to match the test requirements of blades of different sizes and stiffnesses, resulting in poor versatility, and the parameter identification process is easily affected by environmental noise, leading to large errors in the identification results.

[0003] Although some studies have optimized the excitation and response measurement of rotating components using methods such as electromagnet excitation and image acquisition, or conducted aeroelastic stability studies of tiltrotors through wind tunnel testing systems, these technologies mostly focus on specific operating conditions such as a single rotational speed, a fixed tilt angle, or local performance such as flutter boundary prediction. They have failed to develop a comprehensive, interference-resistant, and high-precision excitation test system for identifying tiltrotor blade dynamic parameters that can adapt to multiple operating conditions. This makes it difficult to meet the demand for comprehensive, accurate, and efficient acquisition of blade dynamic parameters in engineering research and development. Therefore, developing an excitation test system that can adapt to combined rotation and tilting operating conditions, possesses strong anti-interference capabilities, and is highly versatile, to achieve accurate identification of blade dynamic parameters, has become a key technological bottleneck that urgently needs to be overcome in the development of tiltrotor technology. Summary of the Invention

[0004] To address the aforementioned shortcomings, this invention aims to solve the problems existing in the prior art by providing a vibration test system for identifying the dynamic parameters of tiltrotor blades. This system is compact, easy to operate, and can achieve precise positioning of the blade's tilt attitude from 0° to 90° through attitude adjustment. A multi-point coordinated vibration module applies broadband random excitation or sinusoidal frequency sweep excitation as needed. Data analysis identifies core dynamic parameters such as the blade's natural frequency, mode shape, and damping ratio. This invention is suitable for variable operating condition testing of tiltrotor blades, featuring high identification accuracy, strong versatility, and convenient operation. It can effectively shorten the testing cycle, reduce R&D costs, and provide reliable data support for blade structure optimization design and flight safety verification. It has practical engineering value in the field of tiltrotor blade dynamic parameter identification testing technology. The technical solution adopted by this invention is as follows:

[0005] A vibration test system for identifying dynamic parameters of a tilting rotor blade includes a rotor assembly and a tilting assembly. The rotor assembly includes a six-component balance and a reduction gearbox. The six-component balance is a box balance. The six-component balance includes a floating frame and a fixed frame arranged vertically. The floating frame and the fixed frame are connected by several force sensors. The fixed frame is connected to the reduction gearbox. An output gear shaft and an input gear shaft are rotatably arranged on the reduction gearbox. A drive motor is mounted on the reduction gearbox. The output shaft of the drive motor is coaxially connected to the input gear shaft. The teeth of the input gear shaft mesh with the teeth of the output gear shaft.

[0006] A bearing seat is provided on the floating frame, and the rotor shaft is rotatably engaged with the bearing seat. The lower end of the rotor shaft is coaxially connected to the output gear shaft through a torque balance assembly. An mounting sleeve is provided on the bearing seat, and the slide cylinder of the automatic swashplate is slidably fitted onto the mounting sleeve. The upper end of the rotor shaft passes through the mounting sleeve and is connected to the rotor hub. The rotor hub includes a rotor hub shell and several rotor hub arms rotatably mounted on the rotor hub shell. Several circumferentially arranged blades are respectively connected to several rotor hub arms in a one-to-one correspondence. Several rotor hub arms are respectively hinged to the upper ends of several tie rods. The lower ends of several tie rods are respectively hinged to the moving ring of the automatic swashplate. The lower ends of several hydraulic excitation cylinders are respectively hinged to the floating frame, and the upper ends of several hydraulic excitation cylinders are respectively hinged to the fixed ring of the automatic swashplate. An amplifier is installed at the top of the rotor shaft. A slip ring is provided on the reduction gearbox, and the rotor of the slip ring is connected to the output gear shaft. Several force sensors, slip rings, amplifiers, and torque balance assemblies are respectively electrically connected to a data acquisition device. The reduction gearbox is hinged to the tilting assembly.

[0007] Furthermore, the input gear shaft is connected to the output shaft of the drive motor via a diaphragm coupling.

[0008] Furthermore, the amplifier is fixed to the rotor shaft via an amplifier mounting bracket.

[0009] Furthermore, the rotor shaft is a tubular shaft component, and the cables for the torque balance assembly and the slip ring run through the central through hole of the rotor shaft.

[0010] Furthermore, the drive motor is mounted on the gearbox via a motor mounting bracket.

[0011] Furthermore, the tilting assembly includes a frame, with a rotating shaft mounting seat on each side of the frame. Two rotating shaft covers are connected to the two rotating shaft mounting seats respectively, and a hinge hole is formed between the rotating shaft covers and the corresponding rotating shaft mounting seats. The two rotating shaft heads are respectively hinged to the two hinge holes, and the two rotating shaft heads are coaxial. The two sides of the gearbox are respectively connected to the two rotating shaft heads.

[0012] Furthermore, the uprights are installed on the platform.

[0013] Furthermore, the upright frame is provided with a positioning arc plate, and the positioning arc plate is provided with a number of adjusting screw holes arranged around the axis of the hinge hole. The adjusting screw holes at both ends are respectively connected to the axis of the hinge hole at an angle of 90°. The shaft head is connected to one end of the rocker arm, and the other end of the rocker arm extends radially along the shaft head. The rocker arm is provided with an elongated arc hole, and the adjusting screw hole is connected to the elongated arc hole by screws.

[0014] Furthermore, the outer periphery of the positioning arc plate is provided with a sector tooth structure, the rocker arm is provided with a tilting motor, and the output shaft of the tilting motor is provided with a tilting gear, which meshes with the sector tooth structure.

[0015] Furthermore, the rotor assembly also includes a counterweight mounting base and a counterweight block. The counterweight mounting base is connected to the motor mounting base, and the counterweight block is provided on the counterweight mounting base. The counterweight block and the drive motor are arranged on both sides of the rotor shaft axis. The axes of the two rotating shaft heads intersect perpendicularly with the rotor shaft axis. The center of gravity of the rotor assembly is on the rotor shaft axis.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] This invention combines technical adaptability and application applicability, enabling vibration testing of helicopters, fixed-wing aircraft, and tilt-rotor transition flight modes. It supports flexible adjustment of excitation position, amplitude, and frequency, precisely matching the resonance requirements of different blade modes, significantly reducing the interference of added mass and stiffness on the test, and improving data accuracy. Simultaneously, it meets the force measurement requirements under blade rotation conditions, featuring high identification accuracy, strong versatility, and convenient operation. It can effectively shorten the test cycle and reduce R&D costs, providing reliable data support for blade structural optimization design and flight safety verification. It has practical engineering value in the field of tilt-rotor blade dynamic parameter identification testing technology. Attached Figure Description

[0018] Figure 1This is an isometric view of the present invention;

[0019] Figure 2 This is a left sectional view of the present invention;

[0020] Figure 3 It is a sectional view of the gearbox body and the upright frame in tandem;

[0021] Figure 4 yes Figure 3 The left view;

[0022] Figure 5 This is a partial assembly diagram showing how vibration and blade collective pitch angle adjustment are achieved through a hydraulic excitation cylinder.

[0023] Figure 6 This is a schematic diagram of the meshing of the output gear shaft and the input gear shaft;

[0024] Figure 7 This is a schematic diagram of a six-component balance.

[0025] In the diagram, 1. Platform, 2. Stand, 3. Counterweight mounting base, 4. Counterweight block, 5. Motor mounting base, 6. Drive motor, 7. Positioning arc plate, 8. Diaphragm coupling, 9. Gearbox, 10. Six-component balance, 11. Torque balance assembly, 12. Hydraulic excitation cylinder, 13. Bearing housing, 14. Rotor shaft, 15. Amplifier, 16. Amplifier mounting base, 17. Propeller hub, 18. Tie rod, 19. Automatic swashplate, 20. Output gear shaft, 21. Input gear shaft, 22. Slip ring, 23. Rocker arm, 24. Shaft mounting base, 25. Shaft cover, 26. Shaft head, 27. Floating frame, 28. Force sensor, 29. Fixed frame, 30. Mounting sleeve, 31. Propeller hub support arm, 32. Adjusting screw hole, 33. Long arc hole. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is described below with reference to specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0027] The connections mentioned in this invention are divided into fixed connections and detachable connections. Fixed connections, also known as non-detachable connections, include but are not limited to conventional fixed connection methods such as folded connections, riveted connections, adhesive connections, and welded connections. Detachable connections include but are not limited to conventional disassembly methods such as bolted connections, snap-fit ​​connections, pin connections, and hinged connections. When a specific connection method is not explicitly defined, it is assumed that at least one existing connection method can be found to achieve this function, and those skilled in the art can choose according to their needs. For example, a welded connection can be chosen for fixed connections, and a bolted connection can be chosen for detachable connections.

[0028] The present invention will be further described in detail below with reference to the accompanying drawings. The following embodiments are explanations of the present invention, but the present invention is not limited to the following embodiments.

[0029] Example: Figures 1 to 7 As shown, a vibration test system for identifying the dynamic parameters of a tilting rotor blade includes a rotor assembly and a tilting assembly. The rotor assembly includes a six-component balance 10 and a reduction gearbox 9. The six-component balance 10 is a box balance. The six-component balance 10 includes a floating frame 27 and a fixed frame 29 arranged vertically. The floating frame 27 and the fixed frame 29 are connected by several force sensors 28. The fixed frame 29 is connected to the reduction gearbox 9. An output gear shaft 20 and an input gear shaft 21 are rotatably arranged on the reduction gearbox 9. A drive motor 6 is mounted on the reduction gearbox 9. The output shaft of the drive motor 6 is coaxially connected to the input gear shaft 21. The teeth of the input gear shaft 21 mesh with the teeth of the output gear shaft 20.

[0030] A bearing seat 13 is provided on the floating frame 27. The rotor shaft 14 is rotatably engaged with the bearing seat 13. The lower end of the rotor shaft 14 is coaxially connected to the output gear shaft 20 through a torque balance assembly 11. A mounting sleeve 30 is provided on the bearing seat 13. The slide of the automatic swashplate 19 is slidably fitted onto the mounting sleeve 30. The upper end of the rotor shaft 14 passes through the mounting sleeve 30 and is connected to the rotor hub 17. The rotor hub 17 includes a rotor hub shell and a plurality of rotor hub arms 31 rotatably mounted on the rotor hub shell. A plurality of circumferentially arranged blades are respectively connected to a plurality of rotor hub arms 31 in a one-to-one correspondence. The upper ends of several tie rods 18 are hinged, and the lower ends of several tie rods 18 are respectively hinged to the moving ring of the automatic tilter 19. The lower ends of several hydraulic excitation cylinders 12 are respectively hinged to the floating frame 27, and the upper ends of several hydraulic excitation cylinders 12 are respectively hinged to the fixed ring of the automatic tilter 19. The amplifier 15 is installed at the top of the rotor shaft 14. A slip ring 22 is provided on the gearbox 9. The rotor of the slip ring 22 is connected to the output gear shaft 20. Several force sensors 28, slip ring 22, amplifier 15 and torque balance assembly 11 are respectively electrically connected to the data acquisition device. The gearbox 9 is hinged to the tilting assembly.

[0031] The input gear shaft 21 is connected to the output shaft of the drive motor 6 via a diaphragm coupling 8.

[0032] Amplifier 15 is fixed to rotor shaft 14 via amplifier mounting bracket 16.

[0033] The rotor shaft 14 is a tubular shaft component, and the cables of the torque balance assembly 11 and the slip ring 22 are routed through the central through hole of the rotor shaft 14.

[0034] The drive motor 6 is mounted on the gearbox 9 via the motor mounting bracket 5.

[0035] The tilting assembly includes a frame 2, with a rotating shaft mounting seat 24 on each side of the frame 2. Two rotating shaft covers 25 are connected to the two rotating shaft mounting seats 24 respectively, and a hinge hole is formed between the rotating shaft cover 25 and the corresponding rotating shaft mounting seat 24. Two rotating shaft heads 26 are respectively hinged to the two hinge holes, and the two rotating shaft heads 26 are coaxial. The two sides of the gearbox 9 are respectively connected to the two rotating shaft heads 26.

[0036] The upright frame 2 is installed on the platform 1.

[0037] The support frame 2 is provided with a positioning arc plate 7, which is provided with a plurality of adjusting screw holes 32 arranged around the axis of the hinge hole. The adjusting screw holes 32 at both ends are respectively connected to the axis of the hinge hole at an angle of 90°. The shaft head 26 is connected to one end of the rocker arm 23, and the other end of the rocker arm 23 extends radially along the shaft head 26. The rocker arm 23 is provided with an elongated arc hole 33, and the adjusting screw hole 32 is connected to the elongated arc hole 33 by screws.

[0038] The outer periphery of the positioning arc plate 7 is provided with a fan-shaped tooth structure, the rocker arm 23 is provided with a tilting motor, and the output shaft of the tilting motor is provided with a tilting gear, which meshes with the fan-shaped tooth structure.

[0039] The rotor assembly also includes a counterweight mounting base 3 and a counterweight block 4. The counterweight mounting base 3 is connected to the motor mounting base 5. The counterweight block 4 is provided on the counterweight mounting base 3. The counterweight block 4 and the drive motor 6 are arranged on both sides of the axis of the rotor shaft 14. The axes of the two rotating shaft heads 26 intersect perpendicularly with the axis of the rotor shaft 14. The center of gravity of the rotor assembly is on the axis of the rotor shaft 14.

[0040] The rotation axis of the rotor hub 17 and the output shaft of the drive motor 6 are eccentrically arranged through the reduction gearbox 9. A slip ring 22 is installed at the end of the output gear shaft 20 for measuring the rotation signal. The stand 1 is used to support the rotor assembly and the tilting assembly. The stand 1 and the upright 2 are connected by bolts and positioned by cylindrical pins to ensure a fast, reliable, and stable connection. The center line is marked on the upper surface of the stand 1 for installation positioning. The motor mounting base 5 is fastened to the counterweight mounting base 3, the counterweight block 4 is fastened to the counterweight mounting base 3, and the drive motor 6 is bolted to the motor mounting base 5. The position of the drive motor 6 is adjusted by adjusting the set screw.

[0041] The shaft head 26 is mounted on the shaft mounting base 24 and is pressed tightly by the shaft cover 25. The positioning arc plate 7 is fastened to the rocker arm 23. By changing the order of the adjusting screw holes 32 that mate with the long arc hole 33, the rotor assembly can be tilted around the shaft head 26 at an angle range of 0° to 90°. The center height of the shaft head 26 is set in the middle of the entire test system structure. The front and rear weights of the rotor assembly are made the same or basically close by adjusting the counterweight 4, which can reduce the load of tilt angle changes and improve tilt efficiency.

[0042] This embodiment provides three hydraulic excitation cylinders 12, which are evenly arranged circumferentially. The pitch control of the blades is achieved by the extension and retraction of these three cylinders. The system can perform excitation at a frequency of 35Hz and an amplitude of 2mm, or at a frequency of 50Hz and an amplitude of 1mm, meeting experimental requirements. An amplifier 15 is located at the top of the rotor shaft 14, which can be used to amplify, process, and transmit the rotor torque measurement signal and the blade surface strain measurement signal, improving the anti-interference performance and measurement accuracy of the test data.

[0043] The gearbox 9 is securely connected to the motor mounting base 5, using a stop-gauge positioning method to ensure the coaxiality of the motor mounting base 5. The gearbox 9 is also securely connected to the rocker arm 23, using a square stop-gauge positioning method. There are two rocker arms 23, arranged symmetrically on both sides of the gearbox 9. The input gear shaft 21 is splinedly connected to the output shaft of the drive motor 6 via a diaphragm coupling 8. The output gear shaft 20 has a through hole in its center. The torque balance assembly 11 is spatially located in the middle of the six-component balance 10, with their axes coinciding. The lower flange of the bearing housing 13 is securely connected to the floating frame 27, using a stop-gauge positioning method. The floating frame 27 is also securely connected to the bottom of the hydraulic vibration cylinder 12.

[0044] This invention combines technical adaptability and application applicability, enabling vibration testing of helicopters, fixed-wing aircraft, and tilt-rotor transition flight modes. It supports flexible adjustment of excitation position, amplitude, and frequency, precisely matching the resonance requirements of different blade modes, significantly reducing the interference of added mass and stiffness on the test, and improving data accuracy. Simultaneously, it meets the force measurement requirements of the blades in rotational states, featuring high recognition accuracy, strong versatility, and convenient operation. It can effectively shorten the test cycle and reduce R&D costs, providing reliable data support for the structural optimization design and flight safety verification of the blades. It has practical engineering value in the field of blade dynamics parameter identification and testing technology for tilt-rotor aircraft.

[0045] The above embodiments are merely illustrative examples of the present invention and do not limit its scope of protection. Those skilled in the art can make partial changes to them, as long as they do not exceed the spirit and essence of the present invention, they are all within the scope of protection of the present invention.

Claims

1. A vibration test system for identifying the dynamic parameters of a tilting rotor blade, characterized in that: The device includes a rotor assembly and a tilting assembly. The rotor assembly includes a six-component balance (10) and a gearbox (9). The six-component balance (10) is a box balance. The six-component balance (10) includes a floating frame (27) and a fixed frame (29) arranged vertically. The floating frame (27) and the fixed frame (29) are connected by several force sensors (28). The fixed frame (29) is connected to the gearbox (9). An output gear shaft (20) and an input gear shaft (21) are rotatably arranged on the gearbox (9). A drive motor (6) is installed on the gearbox (9). The output shaft of the drive motor (6) is coaxially connected to the input gear shaft (21). The teeth of the input gear shaft (21) mesh with the teeth of the output gear shaft (20). A bearing seat (13) is provided on the floating frame (27). The rotor shaft (14) is rotatably engaged with the bearing seat (13). The lower end of the rotor shaft (14) is coaxially connected to the output gear shaft (20) through a torque balance assembly (11). An mounting sleeve (30) is provided on the bearing seat (13). The slide of the automatic swashplate (19) is slidably fitted onto the mounting sleeve (30). The upper end of the rotor shaft (14) passes through the mounting sleeve (30) and is connected to the rotor hub (17). The rotor hub (17) includes a rotor hub shell and several rotor hub arms (31) rotatably mounted on the rotor hub shell. Several circumferentially arranged blades are respectively connected to several rotor hub arms (31) one by one. Several rotor hub arms (31) are respectively connected to several rotor hub arms (31) one by one. The upper ends of several tie rods (18) are hinged, and the lower ends of several tie rods (18) are respectively hinged to the moving ring of the automatic tilter (19). The lower ends of several hydraulic excitation cylinders (12) are respectively hinged to the floating frame (27). The upper ends of several hydraulic excitation cylinders (12) are respectively hinged to the fixed ring of the automatic tilter (19). The amplifier (15) is installed at the top of the rotor shaft (14). A slip ring (22) is provided on the gearbox (9). The rotor of the slip ring (22) is connected to the output gear shaft (20). Several force sensors (28), slip ring (22), amplifier (15) and torque balance assembly (11) are respectively electrically connected to the data acquisition device. The gearbox (9) is hinged to the tilting assembly.

2. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 1, characterized in that: The input gear shaft (21) is connected to the output shaft of the drive motor (6) via a diaphragm coupling (8).

3. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 1, characterized in that: The amplifier (15) is fixed to the rotor shaft (14) via the amplifier mounting bracket (16).

4. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 1, characterized in that: The rotor shaft (14) is a tubular shaft component, and the cables of the torque balance assembly (11) and the slip ring (22) are routed through the central through hole of the rotor shaft (14).

5. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to any one of claims 1-4, characterized in that: The drive motor (6) is mounted on the gearbox (9) via the motor mounting bracket (5).

6. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 5, characterized in that: The tilting assembly includes a frame (2), with a rotating shaft mounting seat (24) on each side of the frame (2). Two rotating shaft covers (25) are connected to the two rotating shaft mounting seats (24) respectively. A hinge hole is formed between the rotating shaft cover (25) and the corresponding rotating shaft mounting seat (24). Two rotating shaft heads (26) are respectively hinged to the two hinge holes. The two rotating shaft heads (26) are coaxial. The two sides of the gearbox body (9) are respectively connected to the two rotating shaft heads (26).

7. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 6, characterized in that: The stand (2) is installed on the platform (1).

8. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 6, characterized in that: The upright frame (2) is provided with a positioning arc plate (7), and the positioning arc plate (7) is provided with a number of adjusting screw holes (32) arranged around the axis of the hinge hole. The adjusting screw holes (32) at both ends are connected to the axis of the hinge hole at an angle of 90°. The shaft head (26) is connected to one end of the rocker arm (23), and the other end of the rocker arm (23) extends radially along the shaft head (26). The rocker arm (23) is provided with an elongated arc hole (33), and the adjusting screw hole (32) and the elongated arc hole (33) are connected by screws.

9. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 8, characterized in that: The outer periphery of the positioning arc plate (7) is provided with a fan-shaped tooth structure, the rocker arm (23) is provided with a tilting motor, the output shaft of the tilting motor is provided with a tilting gear, and the tilting gear meshes with the fan-shaped tooth structure.

10. The excitation test system for identifying the dynamic parameters of a tilting rotor blade according to claim 6, characterized in that: The rotor assembly also includes a counterweight mounting base (3) and a counterweight block (4). The counterweight mounting base (3) is connected to the motor mounting base (5). The counterweight mounting base (3) is provided with a counterweight block (4). The counterweight block (4) and the drive motor (6) are arranged on both sides of the axis of the rotor shaft (14). The axes of the two rotating shaft heads (26) intersect perpendicularly with the axis of the rotor shaft (14). The center of gravity of the rotor assembly is on the axis of the rotor shaft (14).

Images