CN111879511B - Comprehensive test bed for tail speed reducer in helicopter - Google Patents
Comprehensive test bed for tail speed reducer in helicopter Download PDFInfo
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- CN111879511B CN111879511B CN202010815923.8A CN202010815923A CN111879511B CN 111879511 B CN111879511 B CN 111879511B CN 202010815923 A CN202010815923 A CN 202010815923A CN 111879511 B CN111879511 B CN 111879511B
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- 238000012360 testing method Methods 0.000 title claims abstract description 93
- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 claims abstract description 41
- 230000008569 process Effects 0.000 claims abstract description 41
- 238000005452 bending Methods 0.000 claims abstract description 22
- 230000007246 mechanism Effects 0.000 claims abstract description 19
- 230000001050 lubricating effect Effects 0.000 claims abstract description 6
- 238000010008 shearing Methods 0.000 claims abstract description 4
- 239000003921 oil Substances 0.000 claims description 40
- 238000006073 displacement reaction Methods 0.000 claims description 21
- 230000005540 biological transmission Effects 0.000 claims description 11
- 230000001012 protector Effects 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 6
- 229920000742 Cotton Polymers 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 239000010687 lubricating oil Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000011150 reinforced concrete Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000010521 absorption reaction Methods 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims description 2
- 238000004513 sizing Methods 0.000 claims description 2
- 238000010923 batch production Methods 0.000 abstract description 2
- 238000013095 identification testing Methods 0.000 abstract description 2
- 238000011160 research Methods 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 240000004282 Grewia occidentalis Species 0.000 description 1
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- 238000010586 diagram Methods 0.000 description 1
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- 238000005461 lubrication Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008439 repair process Effects 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
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
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- 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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- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a comprehensive test bed for a middle and tail speed reducer of a helicopter, which comprises a mounting base, a driving system, a tail rotor shaft comprehensive loading system, a tail rotor pitch operation shaft loading system, a tail rotor comprehensive loading hydraulic system, a test electric power loading system, a lubricating system, an electric control system and a dynamic data acquisition system, wherein the mounting base is connected with the driving system; the driving system comprises a driving variable frequency motor, a speed increasing box and a torque sensor; the tail rotor shaft comprehensive loading system comprises a comprehensive loading box body, a comprehensive loading process shaft, a bending moment test loader and a shearing test loader; the tail pitch operation shaft loading system comprises a tail pitch operation oil cylinder, a tail pitch operation loading pressure rod and a tail pitch operation loading oil cylinder. The test bed can be used for scientific research tests, identification tests, batch production acceptance tests, overhaul acceptance tests and other tests of the intermediate speed reducer and the tail speed reducer of the helicopter, and the loading mechanism is safe and reliable, adopts electric power closed circulation and has the energy saving rate of 30-60%.
Description
Technical Field
The invention relates to a testing device of a transmission mechanism, in particular to a comprehensive test bed of a middle and tail speed reducer of a helicopter.
Background
Helicopter transmission systems generally consist of a speed reducer and a transmission shaft, the function of which is to transmit the power and the rotation speed output by the engine to the rotor, the tail rotor and the accessory system of the helicopter as required. The transmission system directly affects the performance and quality of the helicopter, and the service life and reliability of the transmission system are endangered by the helicopter. For most helicopters, the helicopter speed reducer mainly comprises a main speed reducer, an intermediate speed reducer and a tail speed reducer, the speed reducer is very important for the helicopter, and once the speed reducer fails, the helicopter is easy to have disastrous accidents. The main function of the helicopter speed reducer is to transmit the rotary motion of an engine on the helicopter to a rotor wing, a tail rotor and other parts needing transmission, so as to realize the purposes of force transmission, direction change and speed change, wherein the middle and tail speed reducers are used for transmitting part of the power output by the engine to the tail rotor. The helicopter speed reducer needs to carry out a large number of tests from each stage of scheme demonstration, component production, delivery test flight and the like, and the test work is a comprehensive system engineering with high cost and long period. The speed reducer test bed is a very critical part in the development work of the speed reducer, so that the development of a helicopter speed reducer comprehensive test bed is necessary.
Disclosure of Invention
The invention aims to provide a comprehensive test bed suitable for a middle and tail speed reducer in a helicopter transmission system.
The technical scheme adopted by the invention is as follows: a comprehensive test bed for a middle and tail speed reducer of a helicopter comprises a mounting base, a driving system, a tail rotor shaft comprehensive loading system, a tail rotor pitch operation shaft loading system, a tail rotor comprehensive loading hydraulic system, a test electric power loading system, a lubricating system, an electric control system and a dynamic data acquisition system;
The mounting machine base comprises mounting seats respectively used for fixedly mounting a driving system, an intermediate speed reducer test piece, a tail rotor shaft comprehensive loading system and a test electric power loading system;
The driving system comprises a driving variable frequency motor, a speed increasing box and a torque sensor, wherein the driving variable frequency motor is connected with the low-speed end of the speed increasing box through a coupler, the high-speed end of the speed increasing box is connected with the torque rotating speed sensor through the coupler, and the output end of the torque rotating speed sensor is connected with a test piece of the intermediate speed reducer through the coupler; the output end of the middle speed reducer test piece is connected with the tail speed reducer test piece through a coupler, and the output end of the tail speed reducer test piece is connected with the input end of the tail rotor shaft comprehensive loading system through the coupler;
The tail rotor shaft comprehensive loading system comprises a comprehensive loading box body, a comprehensive loading process shaft, a bending moment test loader and a shearing test loader; the comprehensive loading process shaft is a thick-wall high-strength hollow shaft, one end of the comprehensive loading process shaft is connected with the output shaft end of the tail rotor shaft through a flange, and the other end of the comprehensive loading process shaft extends into the comprehensive loading box body; the bending moment test loader comprises a loading cross beam and a bending moment test loading oil cylinder, wherein the loading cross beam is arranged on a comprehensive loading process shaft positioned in a comprehensive loading box body through a self-aligning bearing, two ends of the loading cross beam are respectively sleeved in slide ways at two sides of the comprehensive loading box body, the two bending moment test loading oil cylinders are symmetrically arranged at two sides of the comprehensive loading process shaft, a cylinder body of the bending moment test loading oil cylinder is fixed on the inner wall of the comprehensive loading box body below the loading cross beam, a piston rod of the bending moment test loading oil cylinder is connected with the loading cross beam, and the bending moment test loading oil cylinder is provided with a displacement sensor and a pressure sensor and adjusts pressure, displacement speed and distance through a tail rotor comprehensive loading hydraulic system; the shear test loader comprises a shear loading mechanism and a shear loading oil cylinder, wherein the shear loading mechanism is arranged in the middle of a comprehensive loading process shaft and is close to the upper part of a loading cross beam, the shear loading mechanism is assembled with the comprehensive loading process shaft through a four-ball bearing, the shear loading oil cylinder is arranged on the side wall of a comprehensive loading box body, a piston rod of the shear loading oil cylinder is connected with the shear loading mechanism, a pressure sensor and a displacement sensor are arranged on the shear loading oil cylinder, and the pressure, the displacement distance and the displacement speed are controlled through a tail rotor comprehensive loading hydraulic system;
The tail pitch operation shaft loading system comprises a tail pitch operation oil cylinder, a tail pitch operation loading pressure rod and a tail pitch operation loading oil cylinder; the tail pitch operation oil cylinder is arranged at the tail pitch operation mechanism installation position of the tail speed reducer through a flange, a piston rod of the tail pitch operation oil cylinder is connected with one end of a tail pitch operation rod through a movable joint, the other end of the tail pitch operation rod is connected with a tail pitch operation loading pressure rod, the tail pitch operation loading pressure rod penetrates through a hollow comprehensive loading process shaft, the other end of the tail pitch operation loading pressure rod is connected with a piston rod of the tail pitch operation loading oil cylinder fixed at the top end of the comprehensive loading box body through a movable joint, an axial linear bearing is arranged between the tail pitch operation loading pressure rod and the comprehensive loading process shaft, the tail pitch operation loading pressure rod and the comprehensive loading process shaft synchronously operate and can be axially displaced and adjusted, and the tail pitch operation oil cylinder is provided with a pressure sensor and is used for controlling and adjusting pressure, displacement distance and displacement speed through a tail pitch comprehensive loading hydraulic system;
the comprehensive loading hydraulic system of the tail rotor is used for controlling the hydraulic operation of the comprehensive loading system of the tail rotor shaft and the loading system of the tail rotor pitch operation shaft;
The test electric power loading system comprises a loading motor, a moment protector, a ball cage type universal coupling, a bearing seat, a first bevel gear and a second bevel gear; the loading motor and the comprehensive loading process shaft are horizontally arranged at 90 degrees, the loading motor is connected with the input end of the torque protector through a coupler, the output end of the torque protector is connected with a first bevel gear through a ball cage type universal coupler, the shaft end of the first bevel gear is arranged on a bearing seat, a second bevel gear is arranged on the comprehensive loading process shaft and meshed with the first bevel gear, the loading motor generates power, works and loads, and generated current is provided for a driving motor through an inverter to form an electric power closed loading system;
The lubricating system is used for supplying lubricating oil to each friction part;
The electric control system is used for controlling the operation of each part;
the dynamic data acquisition system is used for acquiring operation test data in real time.
Further, still include mounting base, test flat board, mounting base adopts reinforced concrete to pour as a whole, and vibration-proof ditch has been seted up to its periphery, and vibration-proof ditch intussuseption is filled with damping material, and test flat board is adjusted through the three voussoir and is imitated the adjustment and be fixed on mounting base, the mounting plate seat is fixed on test flat board.
Further, a safety shield is mounted on the exposed portion of the driving member.
Further, the safety protection cover comprises a steel skeleton, a porous inner sleeve plate, a porous outer sleeve plate, sound absorption and insulation cotton and a stainless steel outer protection plate.
The test bed can be used for scientific research tests, identification tests, batch production acceptance tests, acceptance tests after major repair and other tests of the intermediate speed reducer and the tail speed reducer of the helicopter transmission system. The test bed loads the tail reduction output shaft through the tail rotor shaft comprehensive loading system, the loading unit of the tail rotor shaft comprehensive loading system can be independently loaded and can be combined to be loaded, the load value is adjustable from 0 to the maximum value, all loads are equivalent to the center of the tail reduction output shaft/the hub, the tail rotor pitch operation shaft loading system can apply load to the tail rotor pitch operation shaft in the moving process, and the loading mechanism is safe and reliable; the test bed adopts electric power closed circulation, the loading motor generates power and loads work, current is connected with the driving motor power supply system in parallel through the frequency converter inversion system electric control system to supply power to the driving motor, and the energy saving rate is 30-60%.
Drawings
Fig. 1 is a schematic diagram of the front structure of the present invention.
Fig. 2 is a schematic top view of the present invention.
Fig. 3 is a partial structural schematic of the present invention.
Detailed Description
The present invention will be described more fully hereinafter with reference to the accompanying drawings, in which preferred embodiments are shown, for the purpose of illustrating the invention, but the scope of the invention is not limited to the specific embodiments shown.
As shown in fig. 1-3, the comprehensive test bed for the middle and tail speed reducers of the helicopter in the embodiment comprises a mounting base 1, a driving system 2, a tail rotor shaft comprehensive loading system 3, a tail rotor pitch operation shaft loading system 4, a tail rotor comprehensive loading hydraulic system 5, a test electric power loading system 6, a lubricating system, an electric control system and a dynamic data acquisition system.
The mounting machine base 1 comprises mounting bases which are respectively used for fixedly mounting a driving system 1, an intermediate speed reducer test piece 7, a tail speed reducer test piece 8, a tail rotor shaft comprehensive loading system 3 and a test electric power loading system 6; the installation frame is fixed on the test flat board, the test flat board is fixedly arranged on the installation base through a three-wedge shockproof adjusting sizing block, the installation base is integrally poured by reinforced concrete, and vibration-proof grooves are formed in the periphery of the installation base and filled with damping materials.
The driving system 2 comprises a driving variable frequency motor 201, a speed increasing box 202 and a torque sensor 203, wherein the driving variable frequency motor 201 is connected with the low-speed end of the speed increasing box 202 through a coupler, the high-speed end of the speed increasing box 202 is connected with the torque rotation speed sensor 203 through the coupler, and the output end of the torque rotation speed sensor 203 is connected with the intermediate speed reducer test piece 7 through the coupler; the output end of the intermediate speed reducer test piece 7 is connected with the intermediate speed reducer test piece 8 through a coupler, and the output end of the tail speed reducer test piece 8 is connected with the input end of the tail rotor shaft comprehensive loading system 3 through a coupler.
The tail rotor shaft comprehensive loading system 3 comprises a comprehensive loading box 301, a comprehensive loading process shaft 302, a bending moment test loader and a shearing test loader; the comprehensive loading process shaft 302 is a thick-wall high-strength hollow shaft, one end of the comprehensive loading process shaft is connected with the output shaft end of the tail rotor shaft through a flange, and the other end of the comprehensive loading process shaft extends into the comprehensive loading box 301; the bending moment test loader comprises a loading cross beam 303 and a bending moment test loading oil cylinder 304, wherein the loading cross beam 303 is arranged on a comprehensive loading process shaft 302 positioned in a comprehensive loading box body through a self-aligning bearing, two ends of the loading cross beam 303 are respectively sleeved in slide ways at two sides of the comprehensive loading box body, the two bending moment test loading oil cylinders 304 are symmetrically arranged at two sides of the comprehensive loading process shaft 302, a cylinder body of the bending moment test loading oil cylinder 304 is fixed on the inner wall of the comprehensive loading box body below the loading cross beam, a piston rod of the bending moment test loading oil cylinder 304 is connected with the loading cross beam 303, and the bending moment test loading oil cylinder 304 is provided with a displacement sensor and a pressure sensor and adjusts pressure, displacement speed and distance through a tail rotor comprehensive loading hydraulic system 5; the shear test loader comprises a shear loading mechanism 305 and a shear loading oil cylinder 306, wherein the shear loading mechanism 305 is arranged in the middle of the comprehensive loading process shaft 302 and is close to the upper part of the loading cross beam, the shear loading mechanism 305 is assembled with the comprehensive loading process shaft 302 through a four-corner ball bearing, the shear loading oil cylinder 306 is arranged on the side wall of the comprehensive loading box 301, a piston rod of the shear loading mechanism is connected with the shear loading mechanism 305, a pressure sensor and a displacement sensor are arranged on the shear loading oil cylinder 306, and the pressure, the displacement distance and the displacement speed are controlled through a tail rotor comprehensive loading hydraulic system 5.
The tail pitch operation shaft loading system 4 comprises a tail pitch operation oil cylinder 401, a tail pitch operation loading pressure rod 402 and a tail pitch operation loading oil cylinder 403; the tail pitch operating cylinder 401 is mounted at the tail pitch operating mechanism mounting position of the tail speed reducer through a flange, a piston rod of the tail pitch operating cylinder is connected with one end of a tail pitch operating rod through a movable joint, the other end of the tail pitch operating rod is connected with a tail pitch operating loading pressure rod 402, the tail pitch operating loading pressure rod 402 penetrates through a hollow comprehensive loading process shaft 302, the other end of the tail pitch operating loading pressure rod is connected with a piston rod of a tail pitch operating loading cylinder 403 fixed at the top end of the comprehensive loading box 301 through a movable joint, an axial linear bearing is arranged between the tail pitch operating loading pressure rod 402 and the comprehensive loading process shaft 302, the tail pitch operating loading pressure rod 402 and the comprehensive loading process shaft 302 synchronously operate and can be axially displaced and adjusted, the tail pitch operating cylinder 401 is provided with a pressure sensor, and pressure, displacement distance and displacement speed are controlled and adjusted through a tail pitch comprehensive loading hydraulic system 5.
The comprehensive loading hydraulic system 5 for the tail rotor is used for controlling the hydraulic operation of the comprehensive loading system 3 for the tail rotor shaft and the loading system 4 for the tail rotor pitch operation shaft.
The test power loading system 6 comprises a loading motor 601, a moment protector, a ball cage type universal coupling 602, a bearing seat, a first bevel gear 603 and a second bevel gear 604; the loading motor 601 and the comprehensive loading process shaft 302 are horizontally installed at 90 degrees, the loading motor 601 is connected with the input end of the torque protector through a coupler, the output end of the torque protector is connected with the first bevel gear 603 through a ball cage type universal coupler 602, the shaft end of the first bevel gear 603 is installed on a bearing seat, the second bevel gear 604 is installed on the comprehensive loading process shaft 302 and meshed with the first bevel gear 603, the loading motor generates electricity to apply work and load, and generated current is provided for the driving motor through an inverter to be used, so that an electric power closed loading system is formed.
The lubrication system is used for supplying lubricating oil to each friction part.
The electric control system is used for controlling the operation of each part.
The dynamic data acquisition system is used for acquiring operation test data in real time.
Further, a safety shield is arranged at the exposed part of the transmission piece, and comprises a steel skeleton, a porous inner and outer sleeve plate, sound-absorbing and sound-insulating cotton and a stainless steel outer guard plate.
Many modifications and other embodiments of the invention will come to mind to one skilled in the art to which this invention pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. Therefore, it is to be understood that the inventions are not to be limited to the specific embodiments disclosed and that modifications and other embodiments are intended to be included within the scope of the appended claims. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.
Claims (2)
1. A comprehensive test bed for a middle and tail speed reducer of a helicopter is characterized in that: the device comprises a mounting base, a driving system, a tail rotor shaft comprehensive loading system, a tail rotor pitch operation shaft loading system, a tail rotor comprehensive loading hydraulic system, a test electric power loading system, a lubricating system, an electric control system and a dynamic data acquisition system;
The mounting machine base comprises mounting seats respectively used for fixedly mounting a driving system, an intermediate speed reducer test piece, a tail rotor shaft comprehensive loading system and a test electric power loading system;
The driving system comprises a driving variable frequency motor, a speed increasing box and a torque sensor, wherein the driving variable frequency motor is connected with the low-speed end of the speed increasing box through a coupler, the high-speed end of the speed increasing box is connected with the torque rotating speed sensor through the coupler, and the output end of the torque rotating speed sensor is connected with a test piece of the intermediate speed reducer through the coupler; the output end of the middle speed reducer test piece is connected with the tail speed reducer test piece through a coupler, and the output end of the tail speed reducer test piece is connected with the input end of the tail rotor shaft comprehensive loading system through the coupler;
The tail rotor shaft comprehensive loading system comprises a comprehensive loading box body, a comprehensive loading process shaft, a bending moment test loader and a shearing test loader; the comprehensive loading process shaft is a thick-wall high-strength hollow shaft, one end of the comprehensive loading process shaft is connected with the output shaft end of the tail rotor shaft through a flange, and the other end of the comprehensive loading process shaft extends into the comprehensive loading box body; the bending moment test loader comprises a loading cross beam and a bending moment test loading oil cylinder, wherein the loading cross beam is arranged on a comprehensive loading process shaft positioned in a comprehensive loading box body through a self-aligning bearing, two ends of the loading cross beam are respectively sleeved in slide ways at two sides of the comprehensive loading box body, the two bending moment test loading oil cylinders are symmetrically arranged at two sides of the comprehensive loading process shaft, a cylinder body of the bending moment test loading oil cylinder is fixed on the inner wall of the comprehensive loading box body below the loading cross beam, a piston rod of the bending moment test loading oil cylinder is connected with the loading cross beam, and the bending moment test loading oil cylinder is provided with a displacement sensor and a pressure sensor and adjusts pressure, displacement speed and distance through a tail rotor comprehensive loading hydraulic system; the shear test loader comprises a shear loading mechanism and a shear loading oil cylinder, wherein the shear loading mechanism is arranged in the middle of a comprehensive loading process shaft and is close to the upper part of a loading cross beam, the shear loading mechanism is assembled with the comprehensive loading process shaft through a four-ball bearing, the shear loading oil cylinder is arranged on the side wall of a comprehensive loading box body, a piston rod of the shear loading oil cylinder is connected with the shear loading mechanism, a pressure sensor and a displacement sensor are arranged on the shear loading oil cylinder, and the pressure, the displacement distance and the displacement speed are controlled through a tail rotor comprehensive loading hydraulic system;
The tail pitch operation shaft loading system comprises a tail pitch operation oil cylinder, a tail pitch operation loading pressure rod and a tail pitch operation loading oil cylinder; the tail pitch operation oil cylinder is arranged at the tail pitch operation mechanism installation position of the tail speed reducer through a flange, a piston rod of the tail pitch operation oil cylinder is connected with one end of a tail pitch operation rod through a movable joint, the other end of the tail pitch operation rod is connected with a tail pitch operation loading pressure rod, the tail pitch operation loading pressure rod penetrates through a hollow comprehensive loading process shaft, the other end of the tail pitch operation loading pressure rod is connected with a piston rod of the tail pitch operation loading oil cylinder fixed at the top end of the comprehensive loading box body through a movable joint, an axial linear bearing is arranged between the tail pitch operation loading pressure rod and the comprehensive loading process shaft, the tail pitch operation loading pressure rod and the comprehensive loading process shaft synchronously operate and can be axially displaced and adjusted, and the tail pitch operation oil cylinder is provided with a pressure sensor and is used for controlling and adjusting pressure, displacement distance and displacement speed through a tail pitch comprehensive loading hydraulic system;
the comprehensive loading hydraulic system of the tail rotor is used for controlling the hydraulic operation of the comprehensive loading system of the tail rotor shaft and the loading system of the tail rotor pitch operation shaft;
The test electric power loading system comprises a loading motor, a moment protector, a ball cage type universal coupling, a bearing seat, a first bevel gear and a second bevel gear; the loading motor and the comprehensive loading process shaft are horizontally arranged at 90 degrees, the loading motor is connected with the input end of the torque protector through a coupler, the output end of the torque protector is connected with a first bevel gear through a ball cage type universal coupler, the shaft end of the first bevel gear is arranged on a bearing seat, a second bevel gear is arranged on the comprehensive loading process shaft and meshed with the first bevel gear, the loading motor generates power, works and loads, and generated current is provided for a driving motor through an inverter to form an electric power closed loading system;
The lubricating system is used for supplying lubricating oil to each friction part;
The electric control system is used for controlling the operation of each part;
The dynamic data acquisition system is used for acquiring operation test data in real time;
The vibration-proof device comprises a mounting base, a test flat plate, a vibration-proof groove, a vibration-proof plate and a mounting seat, wherein the mounting base is integrally poured by reinforced concrete, the vibration-proof groove is formed in the periphery of the mounting base, a vibration-proof material is filled in the vibration-proof groove, the test flat plate is fixedly mounted on the mounting base through adjustment leveling of a three-wedge vibration-proof adjusting sizing block, and the mounting seat is fixed on the test flat plate;
a safety shield is mounted on the exposed portion of the transmission member.
2. The helicopter tail reducer integrated test stand of claim 1, wherein: the safety protection cover comprises a steel skeleton, a porous inner sleeve plate, a porous outer sleeve plate, sound absorption and insulation cotton and a stainless steel outer protection plate.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010815923.8A CN111879511B (en) | 2020-08-14 | 2020-08-14 | Comprehensive test bed for tail speed reducer in helicopter |
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| CN202010815923.8A CN111879511B (en) | 2020-08-14 | 2020-08-14 | Comprehensive test bed for tail speed reducer in helicopter |
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| CN111879511B true CN111879511B (en) | 2024-05-28 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112478195B (en) * | 2020-11-20 | 2022-09-16 | 中国直升机设计研究所 | Helicopter comprehensive test method |
| CN114955001B (en) * | 2022-06-17 | 2024-05-31 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
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| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN101614615A (en) * | 2009-07-03 | 2009-12-30 | 中国航空动力机械研究所 | Simulative loader of tail reducer of helicopter |
| RU2478194C1 (en) * | 2011-08-26 | 2013-03-27 | Открытое акционерное общество "АВИАЦИОННЫЕ РЕДУКТОРА И ТРАНСМИССИИ - ПЕРМСКИЕ МОТОРЫ" (ОАО "Редуктор - ПМ") | Test bench for main reduction gears of helicopters |
| CN106441841A (en) * | 2016-09-12 | 2017-02-22 | 中国人民解放军海军航空工程学院青岛校区 | Helicopter tail decelerator case fatigue test device |
| CN107764545A (en) * | 2017-09-25 | 2018-03-06 | 上海交通大学 | The Helicopter Main Reducer multi-function test stand of electric feedback |
| CN108362496A (en) * | 2018-04-23 | 2018-08-03 | 湘潭大学 | A kind of hydraulic motor retarder Work condition analogue testing stand and its design method |
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2020
- 2020-08-14 CN CN202010815923.8A patent/CN111879511B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN101614615A (en) * | 2009-07-03 | 2009-12-30 | 中国航空动力机械研究所 | Simulative loader of tail reducer of helicopter |
| RU2478194C1 (en) * | 2011-08-26 | 2013-03-27 | Открытое акционерное общество "АВИАЦИОННЫЕ РЕДУКТОРА И ТРАНСМИССИИ - ПЕРМСКИЕ МОТОРЫ" (ОАО "Редуктор - ПМ") | Test bench for main reduction gears of helicopters |
| CN106441841A (en) * | 2016-09-12 | 2017-02-22 | 中国人民解放军海军航空工程学院青岛校区 | Helicopter tail decelerator case fatigue test device |
| CN107764545A (en) * | 2017-09-25 | 2018-03-06 | 上海交通大学 | The Helicopter Main Reducer multi-function test stand of electric feedback |
| CN108362496A (en) * | 2018-04-23 | 2018-08-03 | 湘潭大学 | A kind of hydraulic motor retarder Work condition analogue testing stand and its design method |
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| CN111879511A (en) | 2020-11-03 |
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