阅读说明：本技术 直升机旋翼系统配套轴承试验机以及方法 (Helicopter rotor system matched bearing testing machine and method ) 是由 陈仁波 张佩思 姜艳红 郭帅 雷鸣浩 徐俊 于 2021-08-27 设计创作，主要内容包括：本发明提供了直升机旋翼系统配套轴承试验机,包括：加载系统；以及双旋翼系统；所述双旋翼系统包括：空心外旋翼轴；内旋翼轴,以及动力单元；通过螺旋桨模拟系统模拟直升飞机不同飞行状态,使不同受力状态的力通过浮摆系统传递给安装有待试验轴承组的双旋翼系统上,进而实现待试验轴承组的性能测试,利用浮摆系统中的浮动钢球,使力传递过程稳定、平滑传递至待试验轴承组,实现真实工况下进行轴承性能测试；利用设于机架一侧的输入端轴承测试系统,实现旋翼轴承与输入端轴承进行同步试验,提高试验效率。(The invention provides a helicopter rotor system matched bearing testing machine, which comprises: loading the system; and a dual rotor system; the dual rotor system includes: a hollow outer rotor shaft; an inner rotor shaft, and a power unit; the helicopter is simulated in different flight states by the propeller simulation system, so that forces in different stress states are transmitted to the double-rotor system provided with the bearing group to be tested through the floating system, the performance test of the bearing group to be tested is further realized, the force transmission process is stably and smoothly transmitted to the bearing group to be tested by using floating steel balls in the floating system, and the bearing performance test is realized under real working conditions; the input end bearing test system arranged on one side of the rack is utilized to realize synchronous test of the rotor bearing and the input end bearing, and the test efficiency is improved.)

1. Supporting bearing testing machine of helicopter rotor system, its characterized in that includes:

a loading system (2); and

the double-rotor system (3), the double-rotor system (3) is connected with the output end of the loading force of the loading system (2);

the dual rotor system (3) comprises:

a hollow outer rotor shaft (33);

the inner rotor shaft (34), the inner rotor shaft (34) is rotatably arranged inside the hollow outer rotor shaft (33); and

a power unit (35), wherein the power unit (35) is used for driving the hollow outer rotor shaft (33) and the inner rotor shaft (34) to rotate;

the loading system (2) simulates different flight states of the helicopter, so that the stress of the different flight states is transmitted to the bearing group to be tested installed on the double-rotor system (3), and then the performance parameter test is carried out on the bearing group to be tested.

2. The helicopter rotor system mating bearing tester of claim 1, wherein the loading system (2) comprises:

a propeller simulation system (21); and

the upper end of the floating and swinging system (22) is connected with the propeller simulation system (21), and the lower end of the floating and swinging system (22) is connected with the double-rotor system (3);

the propeller simulation system (21) comprises:

a buoyant rocker support (211);

the simulation frame (212), the said simulation frame (212) is connected with floating and shaking the body support (211) through the self-aligning bearing; and

the power assemblies (213) are arranged on the simulation frame (212) and used for pushing the simulation frame (212) to swing.

3. The helicopter rotor system mating bearing tester of claim 2, wherein the flyweight system (22) comprises:

the floating swing upper seat (221), the floating swing upper seat (221) is connected with the lower end of the propeller simulation system (21); the lower end of the simulation frame (212) is connected with the floating swing upper seat (221);

the floating swing lower seat (222), and a fifth test bearing (105) is arranged on the floating swing lower seat (222); and

and the rotating body (223) is used for connecting the floating swing upper seat (221) with the floating swing lower seat (222) in a floating manner.

4. The helicopter rotor system mating bearing tester of claim 3, wherein the rotor (223) is a steel ball; a space is formed between the floating swing upper seat (221) and the floating swing lower seat (222), and the rotating body (223) is arranged in the space.

5. A helicopter rotor system mating bearing tester according to any one of claims 1-4, wherein said flyweight system (22) further comprises a radial input end loading unit (224) for radially loading the bearing set to be tested.

6. The helicopter rotor system mating bearing tester of claim 5, wherein the radial input loading unit (224) comprises:

the plurality of groups of loading oil cylinders (2241), the plurality of groups of loading oil cylinders (2241) are uniformly distributed along the circumferential direction of the floating swing lower seat (222); and

the loading sleeve (2242), the loading sleeve (2242) is arranged on the outer diameter of the fifth test bearing (105) installed on the floating swing lower seat (222);

the output end of the loading oil cylinder (2241) acts on the outer diameter of the loading sleeve (2242).

7. The helicopter rotor system mating bearing tester of claim 1, wherein the dual rotor system (3) further comprises:

an upper transition assembly (31); and

a lower transition assembly (32);

the upper end of the hollow outer rotor shaft (33) is connected with the upper transition assembly (31), and the lower end of the hollow outer rotor shaft (33) is rotatably connected with the lower transition assembly (32) through a first test bearing (101) and a second test bearing (102);

the upper end of the inner rotor shaft (34) is rotatably connected with the upper transition assembly (31) through a third test bearing (103), and the lower end of the inner rotor shaft (34) is rotatably connected with the inner wall of the hollow outer rotor shaft (33) through a fourth test bearing (104); and

rotor power unit (35) are located the below of hollow outer rotor axle (33) and interior rotor axle (34) to connect hollow outer rotor axle (33) and interior rotor axle (34) simultaneously, make hollow outer rotor axle (33) and interior rotor axle (34) rotatory simultaneously.

8. The helicopter rotor system mating bearing tester of claim 7, wherein the dual rotor system (3) further comprises an axial input loading unit (36) disposed below the inner rotor shaft (34) to provide axial power to the bearing set to be tested.

9. The helicopter rotor system mating bearing tester of claim 1, further comprising an input end bearing test system (4) for performing a performance test on an input end mounted sixth test bearing (106); it includes:

an input power unit (41);

a bearing mounting unit (42), the bearing mounting unit (42) being connected with an output end of the input power unit (41); and

the input end loading unit (43), the input end loading unit (43) is arranged above the output end of the input power unit (41) and can be in contact with the bearing mounting unit (42);

the input power unit (41) is used for driving a sixth test bearing (106) installed on the bearing installation unit (42) to rotate;

and the input end loading unit (43) loads the rotating bearing and tests the performance parameters of the sixth test bearing (106).

10. A test method for a supporting bearing of a helicopter rotor system is characterized by comprising the following steps:

step one, mounting a bearing group to be tested to a specified position;

secondly, starting a rotor wing power unit (35) to drive an inner rotor wing and an outer rotor wing to rotate;

step three, starting the propeller simulation system (21), and enabling the propeller simulation system (21) to simulate different flight states of the helicopter by controlling the power assemblies (213) at different positions;

fourthly, according to different flight states in the third step, stress in different states is transmitted to a bearing group to be tested through a floating pendulum system (22) to carry out performance test; at the moment, the bearing group to be tested is under the combined action of radial and axial loads;

step five, starting a loading unit (224) at the radial input end, enabling loading oil cylinders (2241) of different groups to act on a fifth test bearing (105), and enabling radial force to be transmitted to a bearing group to be tested through a floating swing lower seat (222) to perform a single radial bearing test;

starting an axial input end loading unit (36), and carrying out axial loading on the bearing group to be tested, wherein the bearing group to be tested bears an axial force;

and step seven, starting the input power unit (41), carrying out radial and axial loading on a sixth test bearing (106) and a seventh test bearing (107) arranged on the bearing mounting unit (42), and carrying out performance test on the sixth test bearing (106) and the seventh test bearing (107).

Technical Field

The invention relates to the technical field of bearing tests, in particular to a helicopter rotor system matched bearing testing machine and a method.

Background

The coaxial dual-rotor helicopter is characterized in that the coaxial dual-rotor helicopter is provided with an upper rotor and a lower rotor which rotate around the same theoretical axis in a positive and reverse direction, because the steering directions are opposite, the torque generated by the two rotors is controlled in flight with unchanged course, the coaxial dual rotors are balanced with each other in the state in the flight of the helicopter, and the unbalanced torque generated by the differential motion of the total distance of the upper rotor and the lower rotor can realize that the course is a lifting surface and the control surfaces of the longitudinal direction, the transverse direction and the navigation direction.

Chinese patent CN 105136459B discloses a combined joint bearing testing machine matched with a swing cylinder type helicopter tail rotor system. A servo driving oil cylinder of the testing machine is fixed on an upper platform through an oil cylinder support, a support sleeve is fixed in the center of the upper platform of a testing machine frame through a bolt, the upper end of an operating rod matched with the support sleeve is in threaded connection with a piston rod of the servo driving oil cylinder, and the lower end of the operating rod is connected with a total distance fork; the loader box body is fixed on the lower platform by bolts, a low-frequency oscillating cylinder is arranged on the loader box body, and the output end of the low-frequency oscillating cylinder is connected with the left end key of the low-frequency oscillating shaft; and the four upright posts are respectively fixed with a pull rod type hydraulic cylinder and a pulley assembly through a hydraulic cylinder bracket and a pulley bracket. The testing machine can meet the comprehensive service life test of the joint bearing combined with the tail rotor of the four-support arm, can accurately simulate real working conditions such as load and motion borne by each joint bearing in work, and has the advantages of compact structure, attractive appearance, convenience in operation and the like.

However, in the technical scheme, the rotor wing simulation is not set according to the working state of the real helicopter, so that the difference between the simulation parameter and the service life parameter in actual use is large, and meanwhile, the simulation does not solve the problem that the force of the propeller is stably transmitted to the bearing to be tested, so that the accuracy of the final service life parameter of the bearing is influenced.

Disclosure of Invention

Aiming at the defects of the prior art, the invention provides a bearing testing machine matched with a helicopter rotor system, wherein different flight states of a helicopter are simulated through a propeller simulation system, so that forces in different stress states are transmitted to a double-rotor system provided with a bearing group to be tested through a floating and swinging system, and further the performance test of the bearing group to be tested is realized; the input end bearing test system arranged on one side of the rack is utilized to realize synchronous test of the rotor bearing and the input end bearing, and the test efficiency is improved.

In order to achieve the purpose, the invention provides the following technical scheme:

supporting bearing testing machine of helicopter rotor system, its characterized in that includes:

loading the system; and

the double-rotor system is connected with the output end of the loading force of the loading system;

the dual rotor system includes:

a hollow outer rotor shaft;

the inner rotor shaft is rotatably arranged inside the hollow outer rotor shaft; and

the power unit is used for driving the hollow outer rotor shaft and the inner rotor shaft to rotate;

the loading system simulates different flight states of the helicopter, so that the stress of the different flight states is transmitted to the bearing group to be tested, which is arranged on the double-rotor system, and the performance parameter test is carried out on the bearing group to be tested.

As an improvement, the loading system comprises:

a propeller simulation system; and

the upper end of the floating and swinging system is connected with the propeller simulation system, and the lower end of the floating and swinging system is connected with the double-rotor system;

the propeller simulation system comprises:

a buoyant rocker support;

the simulation frame is connected with the floating shaking body bracket through a self-aligning bearing; and

the power assemblies are arranged on the simulation frame and used for pushing the simulation frame to swing.

As an improvement, the floatage system includes:

the floating swing upper seat is connected with the lower end of the propeller simulation system; the lower end of the simulation frame is connected with the floating swing upper seat;

the fifth test bearing is arranged on the floating swing lower seat; and

the rotor, the rotor is used for floating the connection float swing seat of honour and float swing seat down.

As an improvement, the rotating body is a steel ball; a space is formed between the upper floating swing seat and the lower floating swing seat, and the rotating body is arranged in the space.

As an improvement, the floating pendulum system further comprises a radial input end loading unit for radially loading the bearing group to be tested.

As an improvement, the radial input end loading unit includes:

the plurality of groups of loading oil cylinders are uniformly distributed along the circumferential direction of the floating swing lower seat; and

the loading sleeve is arranged on the outer diameter of a fifth test bearing arranged on the floating swing lower seat;

and the output end of the loading oil cylinder acts on the outer diameter of the loading sleeve.

As an improvement, the dual rotor system further comprises:

an upper transition assembly; and

a lower transition assembly;

the upper end of the hollow outer rotor shaft is connected with the upper transition assembly, and the lower end of the hollow outer rotor shaft is rotatably connected with the lower transition assembly through a first test bearing and a second test bearing;

the upper end of the inner rotor shaft is rotatably connected with the upper transition assembly through a third test bearing, and the lower end of the inner rotor shaft is rotatably connected with the inner wall of the hollow outer rotor shaft through a fourth test bearing; and

the rotor power unit is arranged below the hollow outer rotor shaft and the hollow inner rotor shaft and is simultaneously connected with the hollow outer rotor shaft and the hollow inner rotor shaft, so that the hollow outer rotor shaft and the hollow inner rotor shaft rotate simultaneously.

As an improvement, the double-rotor system further comprises an axial input end loading unit which is arranged below the inner rotor shaft and provides axial power for the bearing group to be tested.

As an improvement, the device also comprises an input end bearing test system for performing performance test on a sixth test bearing installed at the input end; it includes:

an input power unit;

the bearing mounting unit is connected with the output end of the input power unit; and

the input end loading unit is arranged above the output end of the input power unit and can be in contact with the bearing mounting unit;

the input power unit is used for driving a sixth test bearing arranged on the bearing mounting unit to rotate;

and the input end loading unit loads the rotating bearing and tests the performance parameters of the sixth test bearing.

In addition, in order to achieve the above object, the present invention further provides a method for testing a helicopter rotor system mating bearing, which is characterized by comprising the following steps:

step one, mounting a bearing group to be tested to a specified position;

step two, starting a rotor wing power unit to drive an inner rotor wing and an outer rotor wing to rotate;

starting a propeller simulation system, and enabling the propeller simulation system to simulate different flight states of the helicopter by controlling power assemblies at different positions;

fourthly, according to different flight states in the third step, stress in different states is transmitted to a bearing group to be tested through a floating pendulum system, and performance test is carried out; at the moment, the bearing group to be tested is under the combined action of radial and axial loads;

starting a loading unit at the radial input end, enabling loading oil cylinders of different groups to act on a fifth test bearing, transmitting radial force to a bearing group to be tested through a floating swing lower seat, and performing a single radial bearing test;

starting an axial input end loading unit, carrying out axial loading on a bearing group to be tested, and bearing group to be tested bears axial force;

step seven, starting the input power unit, carrying out radial and axial loading on a sixth test bearing and a seventh test bearing which are arranged on the bearing mounting unit, and carrying out performance test on the sixth test bearing and the seventh test bearing;

the fourth step, the fifth step and the sixth step can be combined randomly or carried out independently, and performance tests of different stress states of the bearing group are tested;

and the seventh step is synchronously performed with the first step to the sixth step.

The invention has the beneficial effects that:

(1) the invention simulates different flight states of the helicopter through the propeller simulation system, so that forces in different stress states are transmitted to the double-rotor system provided with the bearing group to be tested through the floating and swinging system, and the force transmission process is stably and smoothly transmitted to the bearing group to be tested by using steel balls in the floating and swinging system, thereby realizing the bearing performance test under the real working condition; the synchronous test of the rotor bearing and the input end bearing is realized by using the input end bearing test system arranged on one side of the rack, so that the test efficiency is improved;

(2) the simulation frame is pushed to swing by the power assemblies of different groups, the force is stably and smoothly transmitted to the bearing to be tested when the simulation frame swings by the arrangement of the rotating body under different motion states of the simulated helicopter, the stress load of the bearing to be tested in a high-speed rotation state is ensured to be consistent with the stress load in actual use, and the accuracy of test data of the bearing to be tested is improved;

(3) the radial loading assembly is used for loading the radial loading seat, so that the fifth test bearing is independently axially loaded, and the performance parameters of the bearing under pure radial load are simulated; meanwhile, the loading system can synchronously load the bearing group to be tested in different states, so that the integrity of the performance index of the bearing group to be tested is further improved;

(4) the axial loading unit is used for axially loading the test bearing group, so that test data of a plurality of groups of test bearing seats in different stress states are realized, the axial loading unit can be independently loaded, and can also be matched with the radial loading unit for loading together to detect the bearing performance parameters in different test states;

(5) the invention simultaneously loads the axial force and the radial force on the sixth test bearing and the seventh test bearing which are arranged on the bearing installation unit through the action of the input power unit and the input end loading unit which are arranged vertically and matched with the conical loading part, and the axial force and the radial force are more matched with the stress working condition of the bearing to be tested, so that the performance parameters of the test bearing when bearing the radial and axial forces are tested are realized; the input end bearing and the rotor bearing are tested synchronously, so that the test efficiency is improved;

(6) according to the invention, the transmission shaft is arranged in a hollow manner, the inner contour is matched with the outer contour, the eccentric vibration caused by self-weight rotation in the rotation process of the transmission shaft is reduced, the variable of the experimental process is reduced, and the accuracy and pertinence of data acquisition in the experimental process are improved;

in conclusion, the invention has the advantages of high test precision, more conformity between bearing stress and actual working conditions, high test efficiency, more complete bearing performance indexes and the like.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a cross-sectional view taken at A-A of FIG. 1 in accordance with the present invention;

FIG. 3 is a cross-sectional view of the loading system configuration of the present invention;

FIG. 4 is an enlarged view of a portion of FIG. 3 at B according to the present invention;

FIG. 5 is a schematic view of the floating swing lower base of the present invention;

FIG. 6 is a schematic view of the floating swing upper seat structure of the present invention;

FIG. 7 is a schematic view of a propeller simulation system according to the present invention;

FIG. 8 is a schematic view of a propeller simulation system according to the present invention in a stressed state when loaded;

FIG. 9 is a first structural schematic view of a dual rotor system of the present invention;

figure 10 is a cross-sectional view of a dual rotor system of the present invention;

FIG. 11 is a second schematic structural view of a dual rotor system of the present invention;

FIG. 12 is an enlarged view of a portion of FIG. 10 at D in accordance with the present invention;

FIG. 13 is an enlarged view of a portion of the invention at E in FIG. 10;

FIG. 14 is an enlarged view of a portion of the invention shown in FIG. 10 at F;

FIG. 15 is a cross-sectional view of an input end bearing test system according to the present invention;

fig. 16 is a schematic structural view of a bearing mounting unit of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and for simplicity of description, and do not indicate or imply that the designated device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

Example one

As shown in fig. 1-3, a helicopter rotor system mating bearing tester comprises:

the device comprises a frame 1, wherein a main machine shell 11 is arranged on the frame 1;

the loading system 2 is arranged below the top of the rack 1; and

the dual-rotor system 3 is arranged in the main machine shell 11 and is connected with the output end of the loading force of the loading system 2;

the loading system 2 includes:

the upper end of the propeller simulation system 21 is connected with the top of the rack 1; and

the upper end of the floating and swinging system 22 is connected with the propeller simulation system 21 in a floating mode, and the lower end of the floating and swinging system 22 is connected with the double-rotor system 3;

the propeller simulation system 21 simulates different flight states of the helicopter, such as vertical motion, pitching motion, yawing motion, leaning motion, back-and-forth motion and the like, and is matched with the floating and swinging system 22 to stably and smoothly transmit stress in different flight states to a bearing group to be tested, which is arranged on the dual-rotor system 3, so as to perform a performance parameter test on the bearing group to be tested.

It should be noted that the bearing set to be tested includes a first test bearing 101, a second test bearing 102, a third test bearing 103, a fourth test bearing 104, and a fifth test bearing 105.

As a modification, as shown in fig. 4 to 6, the buoyancy system 22 includes:

the floating swing upper seat 221, wherein the floating swing upper seat 221 is connected with the lower end of the propeller simulation system 21;

the floating swing lower seat 222 is rotatably arranged on the shell; the fifth test bearing 105 is mounted on the floating swing lower seat 222; and

and the rotating body 223 is used for connecting the floating swing upper seat 221 and the floating swing lower seat 222 in a floating mode.

Further, as shown in fig. 4-6, the rotating body 223 is a steel ball; a space is formed between the upper floating swing seat 221 and the lower floating swing seat 222, and the rotating body 223 is arranged in the space;

the space is composed of a groove a2211 arranged on the floating swing upper seat 221 and a groove b2221 arranged on the floating swing lower seat 222; the grooves a2211 and b2221 are arranged to match the outer shape of the rotating body 223.

It should be noted that the steel ball matching groove a2211 and the groove b2221 connect the floating swing upper seat 221 and the floating swing lower seat 222, so that the force of the floating swing upper seat 221 can be stably and smoothly transmitted to the floating swing lower seat 222, and under the state that the bearing to be tested rotates at a high speed, the stress of the floating swing lower seat 222 is closer to the stress condition of the real load, so that the bearing to be tested can bear the stress condition of the load close to the real state.

Further, in this embodiment, as shown in fig. 5 to 6, an oil hole 2212 penetrating through the center of the floating swing upper seat 221 is formed on the floating swing upper seat 221; the floating swing lower seat 222 is provided with an oil drain hole 2222 penetrating the center of the floating swing lower seat 222.

It should be noted that the upper end of the oil filling hole 2212 is connected with an oil filling nozzle 2223, and lubricating oil is added into the oil filling hole 2212 through the oil filling nozzle 2223, so as to lubricate the steel ball, improve the transmission precision of the steel ball and prolong the service life of the steel ball;

in addition, the oil drain hole 2222 on the lower seat 222 is floated and swung, so that redundant lubricating oil is drained along the oil drain hole 2222, and the lubricating oil is prevented from flowing into the bearing to be tested to influence the test parameters of the bearing to be tested.

Further, as shown in fig. 7 to 8, the propeller simulation system 21 includes:

the floating and shaking body bracket 211 is arranged above the main machine shell 11, and the floating and shaking body bracket 211 is arranged above the main machine shell 11;

the lower end of the simulation frame 212 is connected with the floating swing upper seat 221; the simulation frame 212 is in floating connection with the floating and shaking body bracket 211 through a self-aligning bearing 300; and

the plurality of groups of power assemblies 213 are arranged on the simulation frame 212 and used for pushing the simulation frame 212 to swing; the output end of the power assembly 213 is hinged below the top of the rack 1.

It should be noted that the power assembly 213 preferably adopts a hydraulic oil cylinder pushing manner, and different working states of the propeller, such as forward, backward, in-situ rotation, lateral flying, etc., are simulated by pushing of different power assemblies 213; of course, the power assembly 213 is not limited to hydraulic oil cylinder, and other modes for realizing linear motion may be adopted, such as air cylinder, linear guide transmission, rack transmission, and the like.

In addition, as shown in fig. 4, the floating pendulum system 22 further includes a radial input end loading unit 224 disposed above the main machine housing 11 for radially loading the bearing set to be tested;

the radial input side loading unit 224 includes:

a plurality of groups of loading oil cylinders 2241, wherein the plurality of groups of loading oil cylinders 2241 are uniformly distributed along the circumferential direction of the main machine shell 11; and

the loading sleeve 2242 is arranged on the outer diameter of the fifth test bearing 105 arranged on the floating swing lower seat 222;

the output end of the loading oil cylinder 2241 acts on the outer diameter of the loading sleeve 2242.

It should be noted that, the plurality of groups of loading oil cylinders 2241 are preferably set to four groups, and the fifth test bearing is loaded through different directions, so as to simulate performance parameters of the bearing in different stress states.

Further, as shown in fig. 7, the power assemblies 213 are preferably provided in eight groups, and different groups of power assemblies 213 are selected for providing different test forces according to the helicopter with different weights applied to different test bearings.

It should be noted that the power assemblies 213 of different groups push the simulation frame 212 to swing, so that the stress of the simulation frame 212 is transferred to the floating swing upper seat 221, the rotating body 223 receives the downward tilting force and transfers the force to the floating swing lower seat 222, and the floating swing lower seat 222 transfers the force to the bearing to be tested, so that the stress of the bearing to be tested is as shown in fig. 8, the stress on one side is H, the stress on the symmetrical side is F, so that the stress of the bearing is completely matched with the stress in actual use, and the simulation accuracy of the bearing to be tested is improved.

Example two

As shown in fig. 9 to 14, in which the same or corresponding components as those in the first embodiment are denoted by the same reference numerals as those in the first embodiment, only the points of difference from the first embodiment will be described below for the sake of convenience. The second embodiment is different from the first embodiment in that:

in the present embodiment, as shown in fig. 9 to 11, the dual rotor system 3 includes:

an upper transition assembly 31, wherein the upper transition assembly 31 is connected with the upper part of the main machine shell 11;

a lower transition assembly 32, wherein the lower transition assembly 32 is connected with the lower part of the main machine shell 11;

the upper end of the hollow outer rotor shaft 33 is connected with the connecting seat 313 of the upper transition assembly 31, and the lower end of the hollow outer rotor shaft 33 is rotatably connected with the lower transition assembly 32 through a first test bearing 101 and a second test bearing 102;

the upper end of the inner rotor shaft 34 is rotatably connected with the upper transition assembly 31 through a third test bearing 103, and the lower end of the inner rotor shaft 34 is rotatably connected with the inner wall of the hollow outer rotor shaft 33 through a fourth test bearing 104; and

rotor power pack 35, rotor power pack 35 locates the below of hollow outer rotor shaft 33 and interior rotor shaft 34 to connect hollow outer rotor shaft 33 and interior rotor shaft 34 simultaneously, make hollow outer rotor shaft 33 and interior rotor shaft 34 rotatory simultaneously.

It should be noted that in the present embodiment, the rotor power unit 35 drives the inner rotor shaft 34 and the hollow outer rotor shaft 33 to rotate simultaneously, so as to perform synchronous parameter test on the bearing group to be tested, where the inner ring and the outer ring of the third test bearing 103 and the fourth test bearing 104 both rotate.

As a modification, as shown in fig. 11, the rotor power unit 35 includes:

a first driving part 351, wherein the first driving part 351 is arranged below the main machine housing 11;

a first driving gear 352, wherein the first driving gear 352 is sleeved at the lower end of the hollow outer rotor shaft 33, and the outer diameter of the first driving gear 352 is in meshing transmission with the output end of the first driving part 351;

a second driving unit 353, wherein the second driving unit 353 is disposed below the main body housing 11;

the second driving gear 354 is sleeved at the lower end of the inner rotor shaft 34, and the outer diameter of the second driving gear 354 is in meshing transmission with the output end of the second driving part 353; and

and a first thrust bearing 355, wherein the first thrust bearing 355 is disposed between the first driving gear 352 and the second driving gear 354 and connects the first driving gear 352 and the second driving gear 354.

In addition, the inner diameter of the first driving gear 352 is connected with the outer diameter of the hollow outer rotor shaft 33 through a spline, so that the stability of the hollow outer rotor shaft 33 in the operation process is improved;

the inner diameter of the second driving gear 354 is connected with the outer diameter of the inner rotor shaft 34 through a spline, so that the stability of the inner rotor shaft 34 in the operation process is improved.

As shown in fig. 12, the upper transition assembly 31 includes:

an upper transition seat 311, wherein the upper transition seat 311 is connected with the main machine housing 11;

rotor bearing block 312, said rotor bearing block 312 being connected to said upper transition block 311; and

the outer diameter surface of the connecting seat 313 is connected with the rotor bearing seat 312 in a rotating mode through the test accompanying bearing 200, the upper end of the inner diameter surface of the connecting seat 313 is connected with the outer ring of the third test bearing 103, and the lower end of the inner diameter surface of the connecting seat 313 is connected with the outer diameter surface of the upper end of the hollow outer rotor shaft 33.

Further, as shown in fig. 13, the lower transition assembly 32 includes:

a lower transition seat 321, wherein the lower transition seat 321 is connected with the main machine housing 11; and

the outer diameter surface of the outer rotor support seat 322 is connected with the lower transition seat 321, the upper end of the inner diameter surface of the outer rotor support seat 322 is connected with the outer ring of the first test bearing 101, and the lower end of the inner diameter surface of the outer rotor support seat 322 is connected with the outer ring of the second test bearing 102.

In this embodiment, as shown in fig. 14, the dual rotor system 3 further includes an axial input end loading unit 36 disposed below the inner rotor shaft 34 for providing axial power to the bearing set to be tested.

Preferably, as shown in fig. 14, the axial input end loading unit 36 includes:

an axial carrier 361, wherein the axial carrier 361 is arranged at the bottom end of the inner rotor shaft 34 and is in contact with the lower end of the second driving gear 354;

an axial loading power part 362, the axial loading power part 362 being connected to the housing, and an output end thereof acting on the axial carrier 361.

Further, a spherical groove 3611 is formed at the bottom of the axial bearing body 361; the output end of the axial loading power part 362 is provided with a spherical loading head 3621 matched with the spherical groove 3611.

It should be noted that the axial loading power part 362 is preferably driven by a hydraulic oil cylinder; when the spherical loading head 3621 is used for axially loading the testing device, the force is stably transmitted to the bearing group to be tested by using the spherical loading head 3621.

EXAMPLE III

As shown in fig. 15 to 16, in which the same or corresponding components as those in the first embodiment are denoted by the same reference numerals as those in the first embodiment, only the points of difference from the first embodiment will be described below for the sake of convenience. The third embodiment is different from the first embodiment in that:

in this embodiment, the testing machine further includes an input end bearing testing system 4, where the input end bearing testing system 4 is disposed on the host housing 11 and is used to perform a performance test on a sixth test bearing 106 mounted at an input end; the input end bearing test system 4 includes:

an input power unit 41, wherein the input power unit 41 is arranged at one side of the main machine shell 11;

the bearing mounting unit 42 is connected with the output end of the input power unit 41 through a quincuncial elastic coupling and is arranged on the main machine shell 11; and

an input end loading unit 43, wherein the input end loading unit 43 is arranged above the output end of the input power unit 41 and is in contact with the bearing mounting unit 42;

the input power unit 41 is used for driving the sixth test bearing 106 mounted on the bearing mounting unit 42 to rotate;

the input loading unit 43 loads the rotating bearing and tests the performance parameters of the sixth test bearing 106.

It should be noted that the sixth test bearing 106 includes a set of bearings, one of which is a ball bearing 1061, and the other of which is a cylindrical roller bearing 1062.

Further, the axis of the input end loading unit 43 and the axis of the input power unit 41 are arranged perpendicular to each other.

It should be noted that the input end loading unit 43 and the input power unit 41 which are arranged perpendicular to each other are matched with the loading portion 4221 which is arranged in a conical shape, so that the acting force applied to the test bearing is more stable, the force applied is easier to control, and the accuracy of test data is improved.

In this embodiment, as shown in fig. 16, the bearing mounting unit 42 includes:

an input bearing seat 421, wherein the input bearing seat 421 penetrates through the side wall of the main machine housing 11 and is installed on the main machine housing 11, and the inner diameter of the input bearing seat 421 is used for installing the sixth test bearing 106; a bearing bush 4211 is arranged between the input bearing seat 421 and the sixth test bearing 106 to prevent the inner diameter of the input bearing seat 421 from being worn;

a transmission shaft 422, one end of the transmission shaft 422 is connected with the output end of the input power unit 41, and the transmission shaft 422 is rotatably linked with the input bearing seat 421 through a sixth test bearing 106; the other end of the transmission shaft 422 is provided with a conical loading part 4221; and

the isolation pad 423 is arranged between the loading block and the mounting plate 111 and used for isolating and supporting the loading block, so that the loading block moves to one side after being stressed, and meanwhile, the phenomenon that the mounting plate 111 is abraded after being stressed to influence the service life of equipment is avoided; the loading block is preferably made of polytetrafluoroethylene.

As shown in fig. 15, an installation plate 111 for installing the seventh test bearing 107 is provided in the main housing, and the other end of the transmission shaft 422 is rotatably connected to the seventh test bearing 107.

As a modification, as shown in fig. 15, the input loading unit 43 includes:

a loading power unit 431, wherein the loading power unit 431 is arranged on the main machine shell 11, and the output end of the loading power unit 431 is connected with a loading head; and

the loading block 432 is sleeved on the transmission shaft 422 and is matched with the conical loading part 4221, and the output end of the loading power unit 431 acts on the top end of the loading block 432;

the loading power unit 431 is preferably driven by a hydraulic oil cylinder;

the loading block 432 is square in shape, and its inner hole is conical and matched with the conical loading part 4221.

Further, as shown in fig. 15, the transmission shaft 422 is hollow;

it should be noted that the inner diameter shape of the transmission shaft 422 matches with the outer diameter shape, so as to reduce the vibration of the transmission shaft 422 caused by its own weight during the high-speed rotation process, which affects the test result.

Example four

The method for performing the performance test on the matched bearing by adopting the helicopter rotor system matched bearing testing machine in the first to third technical schemes of the embodiment comprises the following steps:

step one, mounting a bearing group to be tested to a specified position;

step two, starting the rotor wing power unit 35 to drive the inner rotor wing and the outer rotor wing to rotate;

step three, starting the propeller simulation system 21, and enabling the propeller simulation system 21 to simulate different flight states of the helicopter by controlling the power assemblies 213 at different positions;

step four, according to different flight states in the step three, stress in different states is transmitted to the bearing group to be tested through the floating pendulum system 22, and performance test is carried out; at the moment, the bearing group to be tested is under the combined action of radial and axial loads;

step five, starting the radial input end loading unit 224, enabling loading oil cylinders 2241 in different groups to act on the fifth test bearing 105, and enabling the radial force to be transmitted to a bearing group to be tested through the floating swing lower seat 222 to carry out a single radial bearing test;

step six, starting the axial input end loading unit 36, carrying out axial loading on the bearing group to be tested, and bearing group to be tested bears axial force;

step seven, starting the input power unit 41, carrying out radial and axial loading on a sixth test bearing 106 and a seventh test bearing 107 arranged on the bearing installation unit 42, and carrying out performance tests on the sixth test bearing 106 and the seventh test bearing 107;

furthermore, the fourth step, the fifth step and the sixth step can be combined randomly or carried out independently, and performance tests of different stress states of the bearing group are tested;

furthermore, the seventh step and the first to sixth steps are carried out synchronously, so that the test efficiency is improved.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.