Helicopter tail rotor blade fatigue test loading device

Abstract

The invention belongs to the technical field of helicopter tail rotor blade testing, and particularly relates to a helicopter tail rotor blade fatigue test loading device which comprises a flange base, a loading mechanism and a loading mechanism. The tail rotor blade is arranged in the mounting mechanism; the interior of the fixing mechanism is connected with the other end of the tail rotor blade; the load testing mechanism is installed at the end, away from the installation mechanism, of the fixing mechanism, the load testing mechanism is arranged, a tail rotor blade test piece is tested through three different forces, centrifugal and aerodynamic loads borne by the helicopter tail rotor blade in the flight state are simulated, accurate and reliable test data are obtained, and the test efficiency is improved. Three load loading points of centrifugation, waving and shimmy are kept at the same point and have sufficient degree of freedom, so that the loaded distribution of the tail rotor blade better simulates a flight state, the angle of the mounting base is adjustable, and different mounting angle requirements can be met.

Description

Technical Field

[0001] This invention belongs to the field of helicopter tail rotor testing technology, specifically a fatigue testing loading device for helicopter tail rotor blades. Background Technology

[0002] The AC332 tail rotor blades generate thrust during operation of the ducted tail rotor, which is used to balance the anti-torque of the main rotor and primarily serves for helicopter directional control. Fatigue testing was conducted on the JW-8 ducted tail rotor blades to obtain their fatigue characteristics, assess their fatigue life, and demonstrate their compliance with the CCAR29.573 airworthiness regulations for transport category rotorcraft.

[0003] The tail rotor blade assembly is modified into a tail rotor blade fatigue test specimen. Circumferential radial constraints are applied to the inner and outer bushings. Bolts within the pitch control rocker arm and tension / torsion bar assembly are fixed. Centrifugal force, flapping force, and oscillation force are applied through the modified and reinforced section. A fatigue testing loading device for helicopter tail rotor blades needs to be designed to realistically simulate the loads experienced during flight and obtain reliable and accurate test data. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the technical solution adopted by this invention to solve its technical problems is: a fatigue testing loading device for helicopter tail rotor blades, comprising: a flange base, one end of which is provided with an installation mechanism;

[0005] Tail rotor blade, which is disposed inside the mounting mechanism;

[0006] A fixing mechanism, the interior of which is connected to the other end of the tail rotor blade;

[0007] A load testing mechanism, wherein the load testing mechanism is installed at the end of the fixed mechanism away from the installation mechanism;

[0008] The fixing mechanism includes:

[0009] The fastener wraps around the tail rotor blade. The fastener has symmetrical clamps on its upper and lower sides. The clamps are fixed to the fastener and the tail rotor blade with screws. The tail rotor blade assembly is shaped and reinforced at the blade tip direction 360mm from the rotation center (reinforcement materials such as fiberglass and adhesive are used). After reinforcement, the upper and lower clamps and pins are used to complete the assembly and fix the tail rotor blade.

[0010] Telescopic rods are symmetrically arranged on the upper and lower sides of the clamping plate;

[0011] The movable slot is installed at the other end of the telescopic rod, and the outer wall of the movable slot is slidably connected to the other end of the telescopic rod. The movable slot is symmetrically distributed around the tail rotor blade.

[0012] A cleaning component, wherein the outer wall of the cleaning component is rotatably connected to the inner wall of the moving groove.

[0013] Furthermore, the fixing mechanism also includes:

[0014] The tail rotor loading adapter is located at one end of the inner wall of the clamping plate away from the installation mechanism. The other end of the tail rotor loading adapter is connected to the load testing mechanism. The positioning hole of the tail rotor loading adapter is aligned with the positioning hole of the test piece. The tail rotor loading adapter and the upper and lower clamping plates of the test piece are connected by the adapter pin and locked with nuts.

[0015] Telescopic column, which is installed on the opposite side of the moving slot.

[0016] Furthermore, the mounting mechanism includes:

[0017] Mounting base, which is connected to flange base;

[0018] The tail rotor blade fixing bracket is installed at the bottom of the inner wall of the mounting base. The tail rotor blade fixing bracket has an outer slotted blade sleeve and an inner slotted blade sleeve inside. The interiors of the outer and inner slotted blade sleeves are in contact with the outer wall of the tail rotor blade. The outer and inner slotted blade sleeves provide circumferential radial constraint on the inner and outer bushing rings, and fix the bolts inside the pitch rocker arm and the tension bar assembly. Centrifugal force, flapping force and oscillation force are applied through the modified and reinforced section of the tail rotor blade assembly.

[0019] Furthermore, the mounting mechanism also includes:

[0020] A torsion bar is used to fix the fork lug, and one end of the torsion bar fixing fork lug is rotatably connected to the inner wall of the mounting base;

[0021] A torsion bar is fixed to the inner wall of a torsion bar fixing fork lug, and the other end of the torsion bar is connected to one end of the tail rotor blade.

[0022] Furthermore, the load testing mechanism includes:

[0023] A centrifugal loading adapter is connected to one end of a tail rotor loading adapter;

[0024] The centrifugal pulley fork is installed at the end of the centrifugal loading adapter away from the tail blade. A pulley is rotatably connected to the inner wall of the centrifugal pulley fork. The centrifugal pulley fork is connected to the centrifugal loading adapter by a thread and locked with a nut. The centrifugal pulley fork and the pulley are connected by a pulley pin and locked with a nut. The force sensor on the centrifugal actuator cylinder has its own fork and pulley. The two pulleys are connected by a steel wire rope.

[0025] Furthermore, the load testing mechanism also includes:

[0026] A waving adapter fork is installed on the outer wall of the tail rotor loading adapter. A waving force transmission adapter is installed on the top of the waving adapter fork. The waving force transmission adapter is connected to the force sensor on the waving actuator cylinder. The waving force transmission adapter and the waving loading fork are connected by threads and locked with nuts.

[0027] A oscillation loading pin is provided, the outer wall of which is inserted into the inner wall of the tail rotor loading adapter.

[0028] Furthermore, the load testing mechanism also includes:

[0029] A rod end bearing is installed on the inner wall of the oscillating loading pin.

[0030] The oscillating force transmission adapter is installed at the end of the rod end bearing away from the oscillating loading pin shaft. The oscillating force transmission adapter is connected to the force sensor on the oscillating actuator cylinder. The threaded end of the rod end bearing is tightened to the oscillating force transmission adapter, and it is connected to the oscillating loading pin shaft through the oscillating pin and locked with a nut.

[0031] Furthermore, the cleaning component includes:

[0032] The housing has a top that is rotatably connected to the inner wall of the moving groove. The bottom of the housing is U-shaped with protrusions on both sides. Its concave surface contacts the wiping plate. A wet cloth strip is installed at the protruding position. A small hole is opened at the bottom of the housing where the wet cloth strip is installed. The cleaning liquid inside the housing enters the wet cloth strip through the small hole.

[0033] A sleeve, which is mounted on top of the housing;

[0034] A support rod is provided on the side of the housing, and a limit plate is installed at the other end of the support rod away from the housing.

[0035] Furthermore, the cleaning component also includes:

[0036] A bent rod, the outer wall of which is slidably connected to the inner wall of the housing;

[0037] A spring, the spring being mounted on the inner wall of the sleeve, the bottom of the spring being connected to the top of the housing;

[0038] A wiping plate is installed at the bottom of the bent rod, and the outer wall of the wiping plate is in contact with the bottom of the housing.

[0039] Furthermore, the cleaning component also includes:

[0040] A wet cloth strip is symmetrically arranged at the bottom of the housing and installed on both sides of the wiping plate;

[0041] A pressing plate is mounted on top of the bent rod.

[0042] The beneficial effects of this invention are as follows:

[0043] 1. This invention sets up a load testing mechanism to test the tail rotor blade test piece with three different forces, simulating the centrifugal and aerodynamic loads on the helicopter tail rotor blade in flight, obtaining accurate and reliable test data. The three load loading points of centrifugal, flapping and oscillation are kept at the same position and have sufficient degrees of freedom, so that the load distribution of the tail rotor blade better simulates the flight state.

[0044] 2. This invention, by setting a fixing mechanism, allows the cleaning component to contact the tail rotor blade surface, enabling the moving groove to drive the cleaning component to clean the tail rotor blade surface and assist in positioning the strain gauge patches so that the strain gauge patches are symmetrically attached to the tail rotor blade. Then, the cleaning component is moved away from the tail rotor blade, allowing the load testing mechanism to apply forces in different directions to the tail rotor blade for testing. The cleaning component keeps the tail rotor blade surface clean and dry quickly, further enhancing the adhesion of the strain gauge patches.

[0045] 3. This invention uses an installation mechanism to fix and lock the torsion bar assembly to the torsion bar fixing fork lug with internal bolts and self-locking nuts. The positioning point of the positioning block on the tail rotor blade fixing bracket is determined according to the installation angle when the mounting base is horizontal. The angle of the mounting base is adjustable to meet different installation angle requirements; and fully meets the requirements of the test outline for fixing and loading.

[0046] 4. This invention incorporates a cleaning component. A damp cloth strip removes oil and dust from the tail rotor blade surface. Pressing the pressing plate moves the bent rod downwards, bringing the wiping plate into contact with the tail rotor blade surface to absorb the cleaning fluid. Releasing the plate allows the spring to automatically reset the bent rod. After cleaning, rotating the housing causes the support rod to contact the limiting plate with the tail rotor blade. The limiting plate positions the strain gauges, allowing testers to symmetrically attach them in four directions (top, bottom, left, and right), ensuring accurate placement and reducing adjustment time. Attached Figure Description

[0047] Figure 1 This is a schematic diagram of the structure of the present invention;

[0048] Figure 2 This is a bottom view of the present invention;

[0049] Figure 3 This is a schematic diagram of the installation mechanism of the present invention;

[0050] Figure 4 This is a schematic diagram of the fixing structure of the present invention;

[0051] Figure 5 This is a schematic diagram of the structure of the clamping plate of the present invention;

[0052] Figure 6 This is a partial structural schematic diagram of the fixing mechanism of the present invention;

[0053] Figure 7 This is a schematic diagram of the load testing mechanism of the present invention;

[0054] Figure 8 This is a schematic diagram of the cleaning component of the present invention;

[0055] Figure 9 This is a cross-sectional view of the cleaning component of the present invention.

[0056] In the diagram: 1. Flange base; 2. Mounting mechanism; 201. Mounting base; 202. Tail rotor blade fixing bracket; 203. Outwardly slotted rotor sleeve; 204. Torque bar; 205. Torque bar fixing fork lug; 206. Inwardly slotted rotor sleeve; 3. Tail rotor blade; 4. Fixing mechanism; 401. Fixing component; 402. Clamping plate; 403. Telescopic rod; 404. Tail rotor blade loading adapter; 405. Moving slot; 406. Telescopic column; 407. Cleaning assembly; 4071. Housing; 4072. Sleeve; 4073. Support rod; 4074. Limiting plate; 4075. Bending rod; 4076. Pressing plate; 4077. Spring; 4078. Wet cloth strip; 4079. Wiping plate; 5. Load testing mechanism; 501. Centrifugal loading adapter; 502. Centrifugal pulley fork; 503. Pulley; 504. Swinging adapter fork; 505. Swinging loading pin; 506. Swinging force transmission adapter; 507. Swinging force transmission adapter; 508. Rod end bearing. Detailed Implementation

[0057] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. The embodiments of the present invention are given for illustrative and descriptive purposes only, and are not intended to be exhaustive or to limit the invention to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art. The embodiments were chosen and described to better illustrate the principles and practical application of the invention, and to enable those skilled in the art to understand the invention and design various embodiments with various modifications suitable for a particular purpose.

[0058] Example 1, please refer to Figures 1-7 The present invention provides a technical solution: a fatigue testing loading device for helicopter tail rotor blades, which is described below.

[0059] Includes: flange base 1, one end of flange base 1 is provided with mounting mechanism 2, flange base 1 is the adapter base on the test equipment;

[0060] Tail rotor blade 3 is located inside the mounting mechanism 2;

[0061] The fixing mechanism 4 is connected internally to the other end of the tail rotor blade 3;

[0062] Load testing mechanism 5 is installed at the end of fixed mechanism 4 away from installation mechanism 2;

[0063] Before the test begins, the tip of the tail rotor blade 3 assembly, located 360 mm from the rotation center, is modified and reinforced (using materials such as fiberglass and adhesive for reinforcement). The modified tail rotor blade 3 fatigue test specimen is then installed in the fixing mechanism 4. The load testing mechanism 5 is then connected to the other end of the tail rotor blade 3 fatigue test specimen. Strain gauges are attached to the test section of the tail rotor blade 3, with the strain gauge wire grid direction along the axis of the tail rotor blade 3. The entire bridge is used to measure the bending moment in the flapping and oscillation directions. The blade fatigue test specimen is then tested by applying forces in different directions to the load testing mechanism 5.

[0064] Fixed mechanism 4 includes:

[0065] The fastener 401 wraps around the tail rotor blade 3. The fastener 401 is symmetrically provided with clamping plates 402 on its upper and lower sides. The clamping plates 402 are fixed to the fastener 401 and the tail rotor blade 3 by screws. The tip part of the tail rotor blade 3 assembly at 360mm from the rotation center is shaped and reinforced (the reinforcement uses materials such as fiberglass and adhesive). After reinforcement, the upper and lower clamping plates 402 and pins are used to complete the assembly and fix the tail rotor blade 3.

[0066] Telescopic rod 403 is symmetrically arranged on the upper and lower sides of clamping plate 402;

[0067] The movable groove 405 is installed at the other end of the telescopic rod 403. The outer wall of the movable groove 405 is slidably connected to the other end of the telescopic rod 403. The movable groove 405 is symmetrically distributed around the tail rotor blade 3.

[0068] The outer wall of the cleaning component 407 is rotatably connected to the inner wall of the moving groove 405.

[0069] The fixed mechanism 4 also includes:

[0070] The tail rotor loading adapter 404 is located on the inner wall of the clamping plate 402 at one end away from the installation mechanism 2. The other end of the tail rotor loading adapter 404 is connected to the load testing mechanism 5. The positioning hole of the tail rotor loading adapter 404 is aligned with the positioning hole of the test piece. The tail rotor loading adapter 404 and the upper and lower clamping plates 402 of the test piece are connected by the adapter pin and locked with nuts.

[0071] Telescopic column 406 is installed on the opposite side of the movable slot 405.

[0072] During installation, the tail rotor blade 3 fatigue test piece is assembled with the upper and lower clamping plates 402 and pins. Then, the telescopic rod 403 is manually extended to bring the cleaning component 407 into contact with the surface of the tail rotor blade 3. The moving groove 405 drives the cleaning component 407 to clean the surface of the tail rotor blade 3 and assists in positioning the strain gauge patches so that the strain gauge patches are symmetrically attached to the tail rotor blade 3. Then, the cleaning component 407 is moved away from the tail rotor blade 3, and the load testing mechanism 5 applies forces to the tail rotor blade 3 in different directions for testing. The cleaning component 407 keeps the surface of the tail rotor blade 3 clean and dry quickly, further enhancing the adhesion of the strain gauge patches.

[0073] Installation mechanism 2 includes:

[0074] Mounting base 201 is connected to flange base 1;

[0075] The tail rotor blade fixing bracket 202 is installed at the bottom of the inner wall of the mounting base 201. The tail rotor blade fixing bracket 202 has an outer slotted blade sleeve 203 and an inner slotted blade sleeve 206 inside. The interiors of the outer slotted blade sleeve 203 and the inner slotted blade sleeve 206 are in contact with the outer wall of the tail rotor blade 3. The outer slotted blade sleeve 203 and the inner slotted blade sleeve 206 provide circumferential radial constraint to the inner and outer bushing rings, and fix the bolts inside the variable pitch rocker arm and the tension bar 204 assembly. Centrifugal force, flapping force and oscillation force are applied through the modified and reinforced section of the tail rotor blade 3 assembly.

[0076] Installation mechanism 2 also includes:

[0077] The pull-torsion bar fixes the fork lug 205, and one end of the pull-torsion bar fixes the fork lug 205 to be rotatably connected to the inner wall of the mounting base 201;

[0078] The torsion bar 204 is fixed to the inner wall of the torsion bar fixing fork lug 205, and the other end of the torsion bar 204 is connected to one end of the tail rotor blade 3.

[0079] First, insert the tension bar fixing fork lug 205 through the positioning hole of the mounting base 201. After locking the angle between the upper surface of the tension bar fixing fork lug 205 and the lower surface of the mounting base 201 to 15.46° using a digital display inclinometer, tighten it with nuts and flat washers. Fix the mounting base 201 to the flange base 1 with 4 bolts. There is a frustum and positioning hole between the mounting base 201 and the flange base 1 for positioning. Adjust the installation angle of the flange base 1 along the axial direction on the test equipment so that the lower surface of the mounting base 201 is in a horizontal position. Tighten the flange base 1.

[0080] First, the inner and outer slotted blade sleeves 203 are installed on the tail rotor blade fixing bracket 202. Then, the positioning block is installed on the tail rotor blade fixing bracket 202 through the positioning holes using positioning pins and nuts to constrain the ball joint of the tail rotor blade 3-component assembly. The mounting base 201 has four positioning holes and a rectangular groove for positioning. The tail rotor blade fixing bracket 202 is installed on the mounting base 201 using four fixing bracket pins and nuts. The test piece is passed through the inner and outer slotted blade sleeves 203. The ball joint on the pitch rocker arm is aligned with the positioning hole on the positioning block. The tension bar 204 assembly is fixed and locked to the tension bar fixing fork lug 205 using inner bolts and self-locking nuts. The positioning point of the positioning block on the tail rotor blade fixing bracket 202 is determined according to the installation angle when the mounting base 201 is in a horizontal state. The angle of the mounting base 201 is adjustable to meet different installation angle requirements; fully meeting the requirements of the test outline for fixing and loading.

[0081] Load testing mechanism 5 includes:

[0082] Centrifugal loading adapter 501 is connected to one end of tail rotor loading adapter 404;

[0083] Centrifugal pulley fork 502 is installed at the end of centrifugal loading adapter 501 away from the tail blade 3, and pulley 503 is rotatably connected to the inner wall of centrifugal pulley fork 502.

[0084] The load testing mechanism 5 also includes:

[0085] A waving adapter fork 504 is installed on the outer wall of the tail rotor loading adapter 404, and a waving force transmission adapter 507 is installed on the top of the waving adapter fork 504.

[0086] The outer wall of the oscillation loading pin 505 is inserted into the inner wall of the tail rotor loading adapter 404. The oscillation loading pin 505 passes through the swing loading fork lug and the centrifugal loading adapter 501 and is locked with a nut.

[0087] The load testing mechanism 5 also includes:

[0088] The rod end bearing 508 is installed on the inner wall of the oscillation loading pin 505;

[0089] The oscillation force transmission adapter 506 is installed at the end of the rod end bearing 508 away from the oscillation loading pin 505.

[0090] The oscillating force transmitter 506 connects to the force sensor on the oscillating actuator cylinder. The threaded end of the rod end bearing 508 is tightened to the oscillating force transmitter 506, and connected to the oscillating loading pin 505 via an oscillating pin, and locked with a nut. The swinging force transmitter 507 connects to the force sensor on the swinging actuator cylinder. The swinging force transmitter 507 is threaded to the swinging loading fork lug and locked with a nut. The centrifugal pulley fork lug 502 is threaded to the centrifugal loading transmitter 501 and locked with a nut. The centrifugal pulley is connected to the centrifugal pulley via a pin on pulley 503. The fork lug 502 and pulley 503 are locked together with a nut. The force sensor on the centrifugal actuator cylinder has its own fork lug and pulley 503. The two pulleys 503 are connected by a steel wire rope. The tail rotor blade 3 test piece is tested by three different forces to simulate the centrifugal and aerodynamic loads on the helicopter tail rotor blade 3 in flight state, and obtain accurate and reliable test data. The three load loading points of centrifugal, flapping and oscillation are kept at the same position and have sufficient degrees of freedom, so that the load distribution of the tail rotor blade 3 better simulates the flight state.

[0091] Example 2, please refer to Figures 1-9 The present invention provides a technical solution: based on embodiment 1, the cleaning component 407 includes:

[0092] The housing 4071 has its top rotatably connected to the inner wall of the moving groove 405. The bottom of the housing 4071 is U-shaped with protrusions on both sides. Its concave surface contacts the wiping plate 4079. A wet cloth strip 4078 is installed at the protruding position. A small hole is opened at the bottom of the housing 4071 where the wet cloth strip 4078 is installed. The cleaning liquid inside the housing 4071 enters the wet cloth strip 4078 through the small hole.

[0093] Sleeve 4072 is installed on top of housing 4071;

[0094] Support rod 4073 is provided on the side of housing 4071, and limit plate 4074 is installed at the other end of support rod 4073 away from housing 4071.

[0095] Cleaning component 407 also includes:

[0096] The outer wall of the bent rod 4075 is slidably connected to the inner wall of the housing 4071;

[0097] Spring 4077 is installed on the inner wall of sleeve 4072, and the bottom of spring 4077 is connected to the top of housing 4071.

[0098] Wiping plate 4079 is installed at the bottom of bent rod 4075, and the outer wall of wiping plate 4079 is in contact with the bottom of housing 4071.

[0099] Cleaning component 407 also includes:

[0100] Wet cloth strips 4078 are symmetrically arranged at the bottom of housing 4071 and installed on both sides of wiping plate 4079;

[0101] Press plate 4076 is installed on top of bent rod 4075.

[0102] Initially, the moving slot 405 is pushed close to the tail rotor blade 3, so that the bottom of the housing 4071 contacts the surface of the tail rotor blade 3. Driven by the telescopic rod 403, the experimental area of ​​the tail rotor blade 3 is thoroughly cleaned. A damp cloth strip 4078 applies the cleaning solution inside the housing 4071 to the surface of the tail rotor blade 3, removing oil and dust. Then, the pressing plate 4076 is pressed, causing the pressing plate 4076 to move the bent rod 4075 downwards, thus moving the wiping plate 4... 079 contacts the surface of the tail rotor blade 3 to absorb the cleaning fluid, then releases it, causing the spring 4077 to automatically drive the bent rod 4075 to return to its original position. After cleaning, rotate the housing 4071 so that the support rod 4073 drives the limiting plate 4074 to contact the tail rotor blade 3. The limiting plate 4074 plays a positioning role for the adhesion of strain gauges, allowing the tester to symmetrically adhere the strain gauges in four positions (up, down, left, and right) to ensure that the strain gauges are aligned vertically, improving the accuracy of the strain gauge position and reducing the adjustment time for strain gauge adhesion.

[0103] The specific workflow is as follows:

[0104] Before the test begins, the tip of the tail rotor blade 3 assembly, located 360 mm from the rotation center, is modified and reinforced (using materials such as fiberglass and adhesive for reinforcement). The modified tail rotor blade 3 fatigue test piece is then installed in the fixing mechanism 4. The load testing mechanism 5 is then connected to the other end of the tail rotor blade 3 fatigue test piece. Strain gauges are attached to the test section of the tail rotor blade 3, with the strain gauge wire grid direction along the axis of the tail rotor blade 3. The entire bridge is used to measure the bending moment in the flapping and oscillation directions. The blade fatigue test piece is then tested by applying forces in different directions to the load testing mechanism 5.

[0105] After installing the tail rotor blade 3, manually extend the telescopic rod 403 to bring the cleaning component 407 into contact with the surface of the tail rotor blade 3. This allows the moving groove 405 to drive the cleaning component 407 to clean the surface of the tail rotor blade 3 and assist in positioning the strain gauge patches. The strain gauge patches are then symmetrically attached to the tail rotor blade 3. Next, move the cleaning component 407 away from the tail rotor blade 3 so that the load testing mechanism 5 can apply forces in different directions to the tail rotor blade 3 for testing. The cleaning component 407 keeps the surface of the tail rotor blade 3 clean and dry quickly, further enhancing the adhesion of the strain gauge patches.

[0106] After installation, the tail rotor blade 3 test piece was tested with three different forces to simulate the centrifugal and aerodynamic loads on the helicopter tail rotor blade 3 in flight, so as to obtain accurate and reliable test data. The three load loading points of centrifugal, flapping and oscillation were kept at the same position and had sufficient degrees of freedom, so that the load distribution of the tail rotor blade 3 could better simulate the flight state. Finally, the test results were recorded.

[0107] Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art and related fields based on the embodiments of the present invention without inventive effort should fall within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described and explained in the present invention, unless otherwise specified or limited, shall be implemented according to conventional means in the art.

Claims

1. A fatigue testing loading device for helicopter tail rotor blades, comprising: A flange base (1), characterized in that: an installation mechanism (2) is provided at one end of the flange base (1); Tail rotor blade (3), the tail rotor blade (3) is disposed inside the mounting mechanism (2); The fixing mechanism (4) is connected to the other end of the tail rotor blade (3); A load testing mechanism (5) is installed at the end of the fixing mechanism (4) away from the installation mechanism (2); The fixing mechanism (4) includes: The fixing member (401) wraps around the tail rotor blade (3). The fixing member (401) is symmetrically provided with clamping plates (402) on its upper and lower sides. The clamping plates (402) are fixed to the fixing member (401) and the tail rotor blade (3) by screws. Telescopic rod (403), the telescopic rod (403) is symmetrically arranged on the upper and lower sides of the clamping plate (402); The movable groove (405) is installed at the other end of the telescopic rod (403). The outer wall of the movable groove (405) is slidably connected to the other end of the telescopic rod (403). The movable groove (405) is symmetrically distributed around the tail rotor blade (3). A cleaning component (407) is provided, the outer wall of which is rotatably connected to the inner wall of a moving groove (405).

2. The fatigue testing loading device for helicopter tail rotor blades according to claim 1, characterized in that: The fixing mechanism (4) also includes: Tail rotor loading adapter (404) is located on the inner wall of the clamp (402) at one end away from the installation mechanism (2), and the other end of the tail rotor loading adapter (404) is connected to the load testing mechanism (5). Telescopic column (406) is installed on the opposite side of the movable slot (405).

3. The helicopter tail rotor blade fatigue testing loading device according to claim 1, characterized in that: The installation mechanism (2) includes: Mounting base (201), which is connected to flange base (1); Tail rotor blade fixing bracket (202) is installed at the bottom of the inner wall of the mounting base (201). The tail rotor blade fixing bracket (202) is provided with an outer slotted blade sleeve (203) and an inner slotted blade sleeve (206). The interiors of the outer slotted blade sleeve (203) and the inner slotted blade sleeve (206) are in contact with the outer wall of the tail rotor blade (3).

4. The helicopter tail rotor blade fatigue testing loading device according to claim 3, characterized in that: The installation mechanism (2) also includes: A torsion bar fixing fork lug (205) is provided, one end of which is rotatably connected to the inner wall of the mounting base (201). A torsion bar (204) is fixed to the inner wall of a torsion bar fixing fork lug (205), and the other end of the torsion bar (204) is connected to one end of the tail rotor blade (3).

5. The helicopter tail rotor blade fatigue testing loading device according to claim 2, characterized in that: The load testing mechanism (5) includes: Centrifugal loading adapter (501), which is connected to one end of tail rotor loading adapter (404); Centrifugal pulley fork (502), the centrifugal pulley fork (502) is installed at the end of the centrifugal loading adapter (501) away from the tail blade (3), and a pulley (503) is rotatably connected to the inner wall of the centrifugal pulley fork (502).

6. The helicopter tail rotor blade fatigue testing loading device according to claim 5, characterized in that: The load testing mechanism (5) also includes: A waving adapter fork (504) is installed on the outer wall of the tail rotor loading adapter (404), and a waving force transmission adapter (507) is installed on the top of the waving adapter fork (504). A oscillation loading pin (505) is inserted into the inner wall of a tail rotor loading adapter (404).

7. The helicopter tail rotor blade fatigue testing loading device according to claim 6, characterized in that: The load testing mechanism (5) also includes: A rod end bearing (508) is mounted on the inner wall of the oscillation loading pin (505); A oscillation force transmission adapter (506) is installed at the end of the rod end bearing (508) away from the oscillation loading pin (505).

8. The helicopter tail rotor blade fatigue testing loading device according to claim 1, characterized in that: The cleaning component (407) includes: The housing (4071) has its top rotatably connected to the inner wall of the movable groove (405); A sleeve (4072) is mounted on top of a housing (4071); A support rod (4073) is provided on the side of the housing (4071), and a limit plate (4074) is installed at the other end of the support rod (4073) away from the housing (4071).

9. The helicopter tail rotor blade fatigue testing loading device according to claim 8, characterized in that: The cleaning component (407) also includes: A bent rod (4075) has its outer wall slidably connected to the inner wall of the housing (4071). A spring (4077) is mounted on the inner wall of a sleeve (4072), and the bottom of the spring (4077) is connected to the top of a housing (4071). Wiping plate (4079) is installed at the bottom of the bent rod (4075), and the outer wall of the wiping plate (4079) is in contact with the bottom of the housing (4071).

10. The helicopter tail rotor blade fatigue testing loading device according to claim 9, characterized in that: The cleaning component (407) also includes: A wet cloth strip (4078) is symmetrically arranged at the bottom of the housing (4071) and the wet cloth strip (4078) is installed on both sides of the wiping plate (4079); Press plate (4076) is mounted on top of the bent rod (4075).

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