CN113514247A - Loading device of rotor wing joint bearing test system - Google Patents
Loading device of rotor wing joint bearing test system Download PDFInfo
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- CN113514247A CN113514247A CN202110997623.0A CN202110997623A CN113514247A CN 113514247 A CN113514247 A CN 113514247A CN 202110997623 A CN202110997623 A CN 202110997623A CN 113514247 A CN113514247 A CN 113514247A
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- 238000012360 testing method Methods 0.000 title claims abstract description 37
- 238000004088 simulation Methods 0.000 claims abstract description 54
- 230000000712 assembly Effects 0.000 claims abstract description 10
- 238000000429 assembly Methods 0.000 claims abstract description 10
- 229910000831 Steel Inorganic materials 0.000 claims description 7
- 239000010959 steel Substances 0.000 claims description 7
- 239000003921 oil Substances 0.000 description 14
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a loading device of a rotor wing joint bearing test system, which is characterized by comprising the following components: the floating swing upper seat is connected with the propeller simulation system; floating and swinging the lower seat; the rotating body is used for connecting the floating swing upper seat and the floating swing lower seat in a floating manner; the propeller simulation system comprises: the simulation frame is arranged on the supporting seat in a floating manner; the power assemblies are used for driving the simulation frame to swing; the power assembly is used for pushing the simulation frame to swing to simulate different working conditions of the helicopter, the floating swing body is used for enabling the swing force of the simulation frame to be stably and smoothly transmitted to the bearing to be tested, the stress load of the bearing to be tested in a high-speed rotating state is consistent with the stress load of the bearing to be tested in practical use, and the accuracy of test data of the bearing to be tested is improved.
Description
Technical Field
The invention relates to the technical field of helicopter rotor bearing tests, in particular to a loading device of a rotor knuckle bearing test system.
Background
The rotor is an important component for changing the moving direction of the helicopter, wherein the rotor bearing bears the stress of alternating load when the rotor works, so that the rotor bearing is worn out, and the service life of the rotor bearing is determined to be important data for ensuring the safety of the helicopter.
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 the pull rod type hydraulic cylinder and the pulley assembly through the hydraulic cylinder bracket and the pulley bracket. The testing machine can meet the comprehensive service life test of the tail rotor matched combined knuckle bearing with the four support arms, can accurately simulate real working conditions such as load and motion borne by each knuckle 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 problem that the accuracy of the final service life parameter of the bearing is influenced by stably transmitting the force of the propeller to the bearing to be tested is not solved by the simulation.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides the loading device of the rotor wing joint bearing test system, the power assembly pushes the simulation frame to advance and swing to simulate different working conditions of the helicopter, the swing force of the simulation frame can be stably and smoothly transmitted to the bearing to be tested by utilizing the rotor, the stress load of the bearing to be tested in a high-speed rotating state is ensured to be consistent with the stress load in actual use, and the accuracy of the test data of the bearing to be tested is improved.
In order to achieve the purpose, the invention provides the following technical scheme:
a loading device of a rotor wing joint bearing test system is characterized by comprising:
the floating swing upper seat is connected with the propeller simulation system;
floating and swinging the lower seat; and
the rotating body is used for connecting the floating swing upper seat and the floating swing lower seat in a floating manner;
the propeller simulation system comprises:
the simulation frame is arranged on the supporting seat in a floating manner; and
and the plurality of groups of power assemblies are used for driving the simulation frame to swing.
As an improvement, the rotating body is a steel ball.
As an improvement, a space is formed between the floating swing upper seat and the floating swing lower seat, and the rotating body is arranged in the space.
As an improvement, the space is composed of a groove a arranged on the floating swing upper seat and a groove b arranged on the floating swing lower seat.
As a modification, the grooves a and b are arranged to match the outer shape of the rotor.
As an improvement, the propeller simulation system further comprises a supporting seat used for supporting the propeller simulation system.
As an improvement, the simulation frame is connected with the supporting seat through a self-aligning bearing.
As an improvement, the inner diameter surface of the self-aligning bearing is simultaneously sleeved on the lower end part of the simulation frame and the upper end part of the floating swing upper seat.
As an improvement, the device also comprises a plurality of groups of radial loading units which are arranged on the supporting seat and used for carrying out radial loading on the bearing to be tested.
As an improvement, the device further comprises a loading sleeve sleeved on the outer diameter surface of the bearing to be tested, the loading sleeve is arranged between the radial loading unit and the bearing to be tested, and the output end of the radial loading unit acts on the outer diameter of the loading sleeve.
The invention has the beneficial effects that:
(1) the invention pushes the simulation frame to swing through the power assemblies of different groups, simulates different working conditions of the propeller of the helicopter under different motion states, and ensures that the swinging force of the simulation frame can be stably and smoothly transmitted to the bearing to be tested through the arrangement of the rotator, thereby ensuring that the stressed load of the bearing to be tested under the high-speed rotation state is consistent with the stressed load in practical use, and improving the accuracy of the test data of the bearing to be tested;
(2) the propeller simulation system is connected with the supporting seat through the self-aligning bearing, so that the propeller simulation system is connected to the supporting seat in a floating manner, and the propeller simulation system can swing conveniently;
(3) according to the invention, through the arrangement of the positioning groove a and the positioning groove b, the inner ring of the self-aligning bearing is simultaneously connected with the simulation frame and the floating swing upper seat and positioned, so that the connection between the simulation frame and the floating swing upper seat is more stable, the phenomenon of dislocation is not easy to occur, the test precision is improved, and the service life of test equipment is prolonged;
(4) according to the invention, the radial loading unit arranged on the supporting seat is used for carrying out pure radial loading on the bearing to be tested or loading the bearing to be tested together with the propeller simulation system, so that parameter data of the bearing to be tested under more working conditions are simulated, and the comprehensiveness of the test data of the bearing to be tested is improved;
in conclusion, the test device has the advantages that the force of the propeller simulation system is stably transmitted to the bearing group to be tested, the test data is accurate, the test precision is high, the parameters of different stress states can be tested, 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 of the overall construction of the present invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 taken along line A-A in accordance with the present invention;
FIG. 4 is a schematic view of the floating swing upper seat structure of 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 a propeller simulation system according to the present invention;
FIG. 7 is an enlarged view of a portion of the present invention shown at B-B in FIG. 3;
FIG. 8 is an enlarged view of a portion of the invention at C-C of FIG. 3;
FIG. 9 is a schematic view of the bearing to be tested in a stressed state.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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 simplicity of description, and do not indicate or imply that the equipment or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered 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 and 2, a loading device of a rotor wing joint bearing test system comprises:
a bracket 1; wherein the bracket 1 is connected with the bottom surface through a pillar or arranged below other supporting pieces;
the shell 2 is arranged below the bracket 1;
further comprising:
the propeller simulation system 4 is arranged below the top of the support 1, and the lower end of the propeller simulation system 4 is arranged on the support base 3 in a floating manner; and
the upper end of the floating and swinging system 5 is connected with the propeller simulation system 4, and the lower end of the floating and swinging system 5 is rotatably arranged on the shell 2;
different flight states of the aircraft rotor wing, such as vertical motion, pitching motion, yawing motion, inclination motion, back-and-forth motion and the like, are simulated through the propeller simulation system 4, so that stress conditions of the aircraft rotor wing in different states are transmitted to the bearing 100 to be tested installed on the floating system 5 through the floating system 5, and the service life test of the bearing 100 to be tested in different stress states is completed;
it should be noted that, as shown in fig. 2, 3, and 9, the power assemblies 42 of different groups push the simulation frame 41 to swing or rotate, so that the stress of the simulation frame 41 is transmitted to the floating swing upper seat 51, the rotating body 53 receives the downward tilting force and transmits the force to the floating swing lower seat 52, and the floating swing lower seat 52 transmits the force to the bearing 100 to be tested, so that the stress of the bearing 100 to be tested is as shown in fig. 9, one side of the bearing is stressed by H, and the symmetrical side of the bearing is stressed by 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.
In this embodiment, as shown in fig. 3, the floating system 5 includes:
the floating swing upper seat 51 is connected with the lower end of the propeller simulation system 4 through the floating swing upper seat 51;
the floating swing lower seat 52 is rotatably arranged on the shell 2; the bearing 100 to be tested is arranged on the floating swing lower seat 52; and
the rotating body 53 is used for connecting the floating swing upper seat 51 and the floating swing lower seat 52 in a floating way;
the lower end of the floating swing lower seat 52 is connected with a bearing implementation system, wherein a driving system (not shown in the figure) for driving the floating swing lower seat 52 to rotate is arranged in the bearing test system.
Preferably, the rotating body 53 is a steel ball.
Further, as shown in fig. 4 and 5, a space is formed between the upper floating swing seat 51 and the lower floating swing seat 52, and the rotating body 53 is disposed in the space;
further, the space is composed of a groove a511 arranged on the floating swing upper seat 51 and a groove b521 arranged on the floating swing lower seat 52;
further, the grooves a511 and b521 are provided to match the outer shape of the rotor 53.
It should be noted that the steel ball is matched with the ball recess a511 and the ball recess b521 to connect the floating swing upper seat 51 and the floating swing lower seat 52, so that the force of the floating swing upper seat 51 can be stably and smoothly transmitted to the floating swing lower seat 52, and under the condition that the bearing to be tested 100 rotates at a high speed, the stress of the floating swing lower seat 52 is closer to the stress condition of the real load, and further, the bearing to be tested 100 can bear the stress condition of the load close to the real condition.
Preferably, the present embodiment further comprises a support base 3 for supporting the propeller simulation system 4; the supporting seat 3 is connected with the shell 2 and arranged above the shell 2; the simulation frame 41 is connected with the supporting seat 3 through the self-aligning bearing 200;
in this embodiment, as shown in fig. 4 and 5, an oil hole 512 penetrating through the center of the floating swing upper seat 51 is formed in the floating swing upper seat 51; the floating swing lower seat 52 is provided with an oil discharge hole 522 penetrating through the center of the floating swing lower seat 52.
It should be noted that the upper end of the oil injection hole 512 is connected with an oil injection nozzle 513, and lubricating oil is added into the oil injection hole 512 through the oil injection nozzle 513 and is used for lubricating the steel ball, so that the transmission precision of the steel ball is improved, and the service life of the steel ball is prolonged;
in addition, the oil discharge hole 522 on the lower seat 52 is floated and swung, so that redundant lubricating oil is discharged along the oil discharge hole 522, and the lubricating oil is prevented from flowing into the bearing 100 to be tested to influence the test parameters of the bearing 100 to be tested; the floating swing lower seat 52 is provided with a bearing mounting position for mounting the bearing 100 to be tested.
In this embodiment, as shown in fig. 6, the propeller simulation system 4 includes:
the simulation frame 41 is arranged on the supporting seat 3 in a floating manner; and
a plurality of groups of power assemblies 42, wherein the plurality of groups of power assemblies 42 are used for driving the simulation frame 41 to swing.
The plurality of groups of power assemblies 42 are arranged on the simulation frame 41 and used for pushing the simulation frame 41 to swing; the output end of the power assembly 42 is hinged below the top of the bracket 1.
It should be noted that the power assembly 42 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 42; of course, the power assembly 42 is not limited to the hydraulic cylinder, and other modes for realizing the linear motion may be adopted, such as an air cylinder, a linear guide transmission, a rack transmission, and the like.
Further, as shown in fig. 4 and 6, the inner diameter surface of the self-aligning bearing 200 is simultaneously fitted over the lower end portion of the simulation frame 41 and the upper end portion of the upper floating swing seat 51;
it should be noted that the bottom outer diameter of the simulation frame 41 is provided with a positioning groove a411 matched with the inner diameter of the self-aligning bearing 200; the outer diameter of the top of the upper floating swing seat 51 is provided with a positioning groove b514 matched with the inner diameter of the self-aligning bearing 200.
In addition, the arrangement of the positioning groove a411 and the positioning groove b514 enables the simulation frame 41 and the floating swing upper seat 51 to be connected with the inner ring of the self-aligning bearing 200 and positioned, so that the connection between the simulation frame 41 and the floating swing upper seat 51 is more stable, the phenomenon of dislocation is not easy to occur, and the test precision and the service life of test equipment are improved.
Example two
As shown in fig. 3 and 8, wherein the same or corresponding components as in the first embodiment are denoted by the same reference numerals as in the first embodiment, only the differences 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 this embodiment, as shown in fig. 3, the loading device further includes a radial loading unit 6 disposed on the support base 3 for radially loading the bearing 100 to be tested.
The test device is characterized by further comprising a loading sleeve 62 sleeved on the outer diameter surface of the bearing 100 to be tested, wherein the loading sleeve 62 is arranged between the radial loading unit 6 and the bearing 100 to be tested, and the output end of the radial loading unit 6 acts on the outer diameter of the loading sleeve 62.
Wherein the radial loading unit 6 comprises:
the plurality of groups of loading oil cylinders 61 are uniformly distributed along the circumferential direction of the supporting seat 3; the output end of the loading oil cylinder 61 acts on the outer diameter of the loading sleeve 62
It should be noted that, the radial loading is performed on the bearing 100 to be tested through different loading cylinders 61, so as to simulate performance parameters of the bearing 100 to be tested in different radial force states;
in addition, four groups of loading oil cylinders 61 are preferably arranged on the supporting seat 3, and radial loading is carried out on the bearing to be tested 100 in different directions, so that performance parameter results of different motion states are realized.
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.
Claims (9)
1. A loading device of a rotor wing joint bearing test system is characterized by comprising:
the floating swing upper seat (51), the floating swing upper seat (51) is connected with the propeller simulation system (4);
a floating swing lower seat (52); and
the rotating body (53) is used for connecting the floating swing upper seat (51) and the floating swing lower seat (52) in a floating mode;
the propeller simulation system (4) comprises:
a simulation frame (41); and
a plurality of groups of power assemblies (42), wherein the plurality of groups of power assemblies (42) are used for driving the simulation frame (41) to swing.
2. The loading unit of a test system for a rotary wing joint bearing according to claim 2, wherein the rotating body (53) is a steel ball.
3. The loading device of a rotary wing joint bearing test system according to any one of claims 1-2, wherein a space is formed between the upper floating swing seat (51) and the lower floating swing seat (52), and the rotating body (53) is disposed in the space.
4. A loading unit of a rotor wing joint bearing test system according to claim 3, characterized in that said space is composed of a groove a (511) provided on said floating swing upper seat (51) and a groove b (521) provided on said floating swing lower seat (52).
5. The loading unit of a rotor knuckle bearing test system according to claim 4, further comprising a support base (3) for supporting the propeller simulation system (4).
6. The loading device of a rotor wing joint bearing test system according to claim 5, characterized in that the dummy frame (41) is connected to the support base (3) by means of a self-aligning bearing (200).
7. The loading device of a rotor wing joint bearing test system according to claim 6, characterized in that the inner diameter surface of the self-aligning bearing (200) is sleeved on the lower end of the simulation frame (41) and the upper end of the floating swing upper seat (51) at the same time.
8. The loading device of a rotor wing joint bearing test system according to claim 7, characterized by further comprising a plurality of sets of radial loading units (6) arranged on the support base (3) for radially loading the bearing (100) to be tested.
9. The loading device of a test system of a rotary wing joint bearing according to claim 8, characterized by further comprising a loading sleeve (62) sleeved on the outer diameter surface of the bearing (100) to be tested, wherein the loading sleeve (62) is arranged between the radial loading unit (6) and the bearing (100) to be tested, and the output end of the radial loading unit (6) acts on the outer diameter of the loading sleeve (62).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110997623.0A CN113514247B (en) | 2021-08-27 | 2021-08-27 | Loading device of rotor joint bearing test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110997623.0A CN113514247B (en) | 2021-08-27 | 2021-08-27 | Loading device of rotor joint bearing test system |
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| Publication Number | Publication Date |
|---|---|
| CN113514247A true CN113514247A (en) | 2021-10-19 |
| CN113514247B CN113514247B (en) | 2024-05-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110997623.0A Active CN113514247B (en) | 2021-08-27 | 2021-08-27 | Loading device of rotor joint bearing test system |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101339094A (en) * | 2008-09-01 | 2009-01-07 | 洛阳工铭机电设备有限公司 | Helicopter automatic tilting device large-sized thin-wall bearing intelligent checking analytical method and device |
| WO2009149971A1 (en) * | 2008-06-12 | 2009-12-17 | Siemens Aktiengesellschaft | Bearing shell for a plain bearing, and device and method for the spatially resolved determination of the temperature of a bearing shell in a plain bearing |
| CN204630716U (en) * | 2015-03-05 | 2015-09-09 | 衢州学院 | One is " helicopter " screw propeller lift proving installation under water |
| JP2016161403A (en) * | 2015-03-02 | 2016-09-05 | 日本精工株式会社 | Workpiece pressure device, and vibration inspection apparatus with the same |
| CN207816597U (en) * | 2017-11-20 | 2018-09-04 | 洛阳工铭机电设备有限公司 | A kind of helicopter auto-bank unit thin-wall bearing testing machine |
| CN215893999U (en) * | 2021-08-27 | 2022-02-22 | 中浙高铁轴承有限公司 | Loading device of rotor wing joint bearing test system |
-
2021
- 2021-08-27 CN CN202110997623.0A patent/CN113514247B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009149971A1 (en) * | 2008-06-12 | 2009-12-17 | Siemens Aktiengesellschaft | Bearing shell for a plain bearing, and device and method for the spatially resolved determination of the temperature of a bearing shell in a plain bearing |
| CN101339094A (en) * | 2008-09-01 | 2009-01-07 | 洛阳工铭机电设备有限公司 | Helicopter automatic tilting device large-sized thin-wall bearing intelligent checking analytical method and device |
| JP2016161403A (en) * | 2015-03-02 | 2016-09-05 | 日本精工株式会社 | Workpiece pressure device, and vibration inspection apparatus with the same |
| CN204630716U (en) * | 2015-03-05 | 2015-09-09 | 衢州学院 | One is " helicopter " screw propeller lift proving installation under water |
| CN207816597U (en) * | 2017-11-20 | 2018-09-04 | 洛阳工铭机电设备有限公司 | A kind of helicopter auto-bank unit thin-wall bearing testing machine |
| CN215893999U (en) * | 2021-08-27 | 2022-02-22 | 中浙高铁轴承有限公司 | Loading device of rotor wing joint bearing test system |
Non-Patent Citations (1)
| Title |
|---|
| 胡占齐 等: "航空关节轴承寿命试验机发展综述", 《轴承》, no. 11, 30 November 2015 (2015-11-30), pages 57 - 63 * |
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| CN113514247B (en) | 2024-05-10 |
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