CN111879511A - Helicopter middle and tail speed reducer comprehensive test bed - Google Patents
Helicopter middle and tail speed reducer comprehensive test bed Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 94
- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 49
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- 238000005452 bending Methods 0.000 claims abstract description 22
- 238000010008 shearing Methods 0.000 claims abstract description 22
- 230000007246 mechanism Effects 0.000 claims abstract description 18
- 238000009434 installation Methods 0.000 claims abstract description 13
- 230000001050 lubricating effect Effects 0.000 claims abstract description 7
- 239000003921 oil Substances 0.000 claims description 43
- 238000006073 displacement reaction Methods 0.000 claims description 20
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- 230000005611 electricity Effects 0.000 claims description 3
- 239000010687 lubricating oil Substances 0.000 claims description 3
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- 239000011150 reinforced concrete Substances 0.000 claims description 3
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- 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
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- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Abstract
The invention discloses a helicopter middle and tail speed reducer comprehensive test bed, which comprises an installation base, a driving system, a tail rotor shaft comprehensive loading system, a tail rotor distance operating 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 installation base is connected with the driving system through a connecting rod; the driving system comprises a driving variable frequency motor, an acceleration 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 propeller pitch operating shaft loading system comprises a tail propeller pitch operating oil cylinder, a tail propeller pitch operating loading pressure rod and a tail propeller pitch operating loading oil cylinder. The test bed can be used for scientific research tests, identification tests, batch production acceptance tests, after-overhaul acceptance tests and the like of the intermediate speed reducer and the tail speed reducer of the helicopter, the loading mechanism is safe and reliable, electric power closed circulation is adopted, and the energy saving rate is 30-60%.
Description
Technical Field
The invention relates to a testing device of a transmission mechanism, in particular to a comprehensive test bed for a middle and tail speed reducer of a helicopter.
Background
The helicopter transmission system is generally composed of a speed reducer and a transmission shaft system, and is used for transmitting the power and the rotating speed output by an engine to a rotor wing, a tail rotor and an accessory system of the helicopter according to requirements. The transmission system directly influences the performance and the quality of the helicopter, and the service life and the reliability of the transmission system are safe and dangerous for 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, disastrous accidents easily occur to the helicopter. 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 components 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 a part of power output by the engine to the tail rotor. A large number of tests are required in each stage of scheme demonstration, part production, delivery test flight and the like of the helicopter speed reducer, and the test work is a system engineering with high cost, long period and comprehensiveness. The reducer test bed is a very critical part in reducer development work, so that the development of a comprehensive test bed for the reducer of the helicopter 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 helicopter middle and tail speed reducer comprehensive test bed comprises an installation base, a driving system, a tail rotor shaft comprehensive loading system, a tail rotor pitch operating 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 base comprises mounting bases which are respectively used for fixedly mounting a driving system, a middle 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-up box and a torque sensor, the driving variable frequency motor is connected with the low-speed end of the speed-up box through a coupler, the high-speed end of the speed-up box is connected with the torque and rotation speed sensor through the coupler, and the output end of the torque and rotation speed sensor is connected with an intermediate speed reducer test piece through the coupler; the output end of the middle reducer test piece is connected with the tail reducer test piece through a coupler, and the output end of the tail reducer test piece is connected with the input end of the tail propeller 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 bending moment test loading oil cylinders, wherein the loading cross beam is arranged on a comprehensive loading process shaft in a comprehensive loading box body through a self-aligning bearing, two ends of the loading cross beam are respectively sleeved in slideways on two sides of the comprehensive loading box body, the two bending moment test loading oil cylinders are symmetrically arranged on two sides of the comprehensive loading process shaft, a cylinder body of each 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 each bending moment test loading oil cylinder is connected with the loading cross beam, each bending moment test loading oil cylinder is provided with a displacement sensor and a pressure sensor, and the pressure, the displacement speed; the shearing test loader comprises a shearing loading mechanism and a shearing loading oil cylinder, wherein the shearing loading mechanism is arranged in the middle of a comprehensive loading process shaft and close to the upper part of a loading cross beam, the shearing loading mechanism is assembled with the comprehensive loading process shaft through a four-corner ball bearing, the shearing loading oil cylinder is arranged on the side wall of a comprehensive loading box body, a piston rod of the shearing loading oil cylinder is connected with the shearing loading mechanism, a pressure sensor and a displacement sensor are arranged on the shearing 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 propeller pitch operating shaft loading system comprises a tail propeller pitch operating oil cylinder, a tail propeller pitch operating loading pressure rod and a tail propeller pitch operating loading oil cylinder; the tail propeller pitch operation oil cylinder is arranged at the installation position of a tail propeller pitch operation mechanism of the tail speed reducer through a flange, a piston rod of the tail propeller pitch operation oil cylinder is connected with one end of a tail propeller pitch operation rod through a movable joint, the other end of the tail propeller pitch operation rod is connected with a tail propeller pitch operation loading pressure rod, the tail propeller pitch operation loading pressure rod penetrates through a hollow comprehensive loading process shaft, the other end of the tail propeller pitch operation loading pressure rod is connected with a piston rod of a tail propeller pitch operation loading oil cylinder fixed at the top end of a comprehensive loading box body through a movable joint, an axial linear bearing is arranged between the tail propeller pitch operation loading pressure rod and the comprehensive loading process shaft, the tail propeller pitch operation loading pressure rod and the comprehensive loading process shaft run synchronously and can perform axial displacement adjustment at the same time, a pressure sensor is arranged on the tail propeller pitch operation oil cylinder, and the;
the tail rotor comprehensive loading hydraulic system is used for hydraulic operation control of a tail rotor shaft comprehensive loading system and a tail rotor pitch operating shaft loading system;
the test electric power loading system comprises a loading motor, a torque protector, a rzeppa universal coupling, a bearing seat, a first bevel gear and a second bevel gear; the loading motor and the comprehensive loading process shaft are installed at 90 degrees horizontally, 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 universal coupler, the shaft end of the first bevel gear is installed on a bearing seat, a second bevel gear is installed on the comprehensive loading process shaft and is meshed with the first bevel gear, the loading motor generates electricity and applies work to load, and the generated current is provided for the 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 device further comprises an installation base and a test flat plate, wherein the installation base is integrally cast by adopting reinforced concrete, anti-vibration grooves are formed in the periphery of the installation base, damping materials are filled in the anti-vibration grooves, the test flat plate is flatly and fixedly arranged on the installation base through the adjustment effect of the three-wedge anti-vibration adjustment sizing block, and the installation base is fixed on the test flat plate.
Furthermore, a safety shield is installed on the exposed part of the transmission member.
Furthermore, the safety protection cover comprises a steel skeleton, a porous inner and outer sleeve plate, sound absorption and insulation cotton and a stainless steel outer protective plate.
The test bed can be used for scientific research tests, identification tests, batch production acceptance tests, after-overhaul acceptance tests and the like of the intermediate speed reducer and the tail speed reducer of the helicopter transmission system. The test bed loads the tail reducing output shaft through the tail rotor shaft comprehensive loading system, a tail rotor shaft comprehensive loading system loading unit can independently load and can carry out combined loading, the load value is adjustable from 0 to the maximum value, all loads are equivalently acted on the center of the tail reducing output shaft/a hub, the tail rotor pitch operating shaft loading system can apply loads to a tail rotor pitch control shaft in the moving process, and a loading mechanism is safe and reliable; the test bed adopts closed circulation of electric power, a loading motor generates power to do work and loads, current is connected in parallel with a driving motor power supply system through a frequency converter inverter 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 front view of the present invention.
Fig. 2 is a schematic top view of the present invention.
Fig. 3 is a partial structural schematic diagram of the present invention.
Detailed Description
In order to facilitate an understanding of the invention, the invention will be described more fully and in detail below with reference to the accompanying drawings and preferred embodiments, but the scope of the invention is not limited to the specific embodiments below.
As shown in fig. 1 to fig. 3, the comprehensive test bed for the mid-tail reducer and the tail reducer of the helicopter according to the present embodiment includes an installation base 1, a driving system 2, a tail rotor shaft comprehensive loading system 3, a tail rotor pitch operating 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 base 1 comprises mounting bases which are respectively used for fixedly mounting the driving system 1, the middle reducer test piece 7, the tail reducer test piece 8, the tail rotor shaft comprehensive loading system 3 and the test electric power loading system 6; the mounting base is fixed on a test flat plate, the test flat plate is horizontally and fixedly mounted on the mounting base through the three-wedge shockproof adjusting sizing block adjusting effect, the mounting base is integrally cast by adopting reinforced concrete, shockproof ditches are formed in the periphery of the mounting base, and shock-absorbing materials are filled in the shockproof ditches.
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 and rotation speed sensor 203 through the coupler, and the output end of the torque and rotation speed sensor 203 is connected with an intermediate speed reducer test piece 7 through the coupler; the output end of the middle reducer test piece 7 is connected with the middle reducer test piece 8 through a coupler, and the output end of the tail reducer test piece 8 is connected with the input end of the tail rotor shaft comprehensive loading system 3 through the coupler.
The tail rotor shaft comprehensive loading system 3 comprises a comprehensive loading box body 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 shaft is connected with the output shaft end of the tail rotor shaft through a flange, and the other end of the shaft extends into the comprehensive loading box body 301; the bending moment test loader comprises a loading cross beam 303 and bending moment test loading oil cylinders 304, wherein the loading cross beam 303 is installed on a comprehensive loading process shaft 302 in a comprehensive loading box body through a self-aligning bearing, two ends of the loading cross beam 303 are respectively sleeved in slideways on two sides of the comprehensive loading box body, the two bending moment test loading oil cylinders 304 are symmetrically arranged on 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 is connected with the loading cross beam 303, the bending moment test loading oil cylinder 304 is provided with a displacement sensor and a pressure sensor, and the pressure, the displacement speed and; the shear test loader comprises a shear loading mechanism 305 and a shear loading oil cylinder 306, wherein the shear loading mechanism 305 is installed in the middle of a comprehensive loading process shaft 302 and is close to the upper part of a 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 installed on the side wall of a comprehensive loading box body 301, a piston rod of the shear loading oil cylinder 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 operating shaft loading system 4 comprises a tail pitch operating oil cylinder 401, a tail pitch operating loading pressure rod 402 and a tail pitch operating loading oil cylinder 403; the tail rotor pitch operating cylinder 401 is installed at the installation position of a tail rotor pitch operating mechanism of the tail speed reducer through a flange, the piston rod of the tail-rotor pitch operation rod is connected with one end of the tail-rotor pitch operation rod through a movable joint, the other end of the tail-rotor pitch operation rod is connected with a tail-rotor pitch operation loading pressure rod 402, the tail-rotor pitch operation loading pressure rod 402 penetrates through the hollow comprehensive loading process shaft 302, the other end of the tail-rotor pitch operation loading pressure rod is connected with the piston rod of a tail-rotor pitch operation loading oil cylinder 403 fixed at the top end of the comprehensive loading box body 301 through the movable joint, an axial linear bearing is arranged between the tail-rotor pitch operation loading pressure rod 402 and the comprehensive loading process shaft 302, the tail-rotor pitch operation loading pressure rod 402 and the comprehensive loading process shaft, meanwhile, axial displacement adjustment can be carried out, a pressure sensor is arranged at the tail rotor distance operation oil cylinder 401, and pressure, displacement distance and displacement speed are controlled and adjusted through a tail rotor comprehensive loading hydraulic system 5.
And the tail rotor comprehensive loading hydraulic system 5 is used for controlling the hydraulic operation of the tail rotor shaft comprehensive loading system 3 and the tail rotor pitch operating shaft loading system 4.
The test electric power loading system 6 comprises a loading motor 601, a torque protector, a Rzeppa 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 installed at 90 degrees horizontally, 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 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 is meshed with the first bevel gear 603, the loading motor generates electricity and applies work for loading, and the generated current is provided for the 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.
Furthermore, a safety protection cover is arranged on the exposed part of the transmission part, and the safety protection cover comprises a steel skeleton, a porous inner and outer sleeve plate, sound absorption and insulation cotton and a stainless steel outer protective 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 (4)
1. The utility model provides a helicopter middle and tail reduction gear integrated test platform which characterized in that: the device comprises an installation base, a driving system, a tail rotor shaft comprehensive loading system, a tail rotor distance operating 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 base comprises mounting bases which are respectively used for fixedly mounting a driving system, a middle 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-up box and a torque sensor, the driving variable frequency motor is connected with the low-speed end of the speed-up box through a coupler, the high-speed end of the speed-up box is connected with the torque and rotation speed sensor through the coupler, and the output end of the torque and rotation speed sensor is connected with an intermediate speed reducer test piece through the coupler; the output end of the middle reducer test piece is connected with the tail reducer test piece through a coupler, and the output end of the tail reducer test piece is connected with the input end of the tail propeller 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 bending moment test loading oil cylinders, wherein the loading cross beam is arranged on a comprehensive loading process shaft in a comprehensive loading box body through a self-aligning bearing, two ends of the loading cross beam are respectively sleeved in slideways on two sides of the comprehensive loading box body, the two bending moment test loading oil cylinders are symmetrically arranged on two sides of the comprehensive loading process shaft, a cylinder body of each 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 each bending moment test loading oil cylinder is connected with the loading cross beam, each bending moment test loading oil cylinder is provided with a displacement sensor and a pressure sensor, and the pressure, the displacement speed; the shearing test loader comprises a shearing loading mechanism and a shearing loading oil cylinder, wherein the shearing loading mechanism is arranged in the middle of a comprehensive loading process shaft and close to the upper part of a loading cross beam, the shearing loading mechanism is assembled with the comprehensive loading process shaft through a four-corner ball bearing, the shearing loading oil cylinder is arranged on the side wall of a comprehensive loading box body, a piston rod of the shearing loading oil cylinder is connected with the shearing loading mechanism, a pressure sensor and a displacement sensor are arranged on the shearing 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 propeller pitch operating shaft loading system comprises a tail propeller pitch operating oil cylinder, a tail propeller pitch operating loading pressure rod and a tail propeller pitch operating loading oil cylinder; the tail propeller pitch operation oil cylinder is arranged at the installation position of a tail propeller pitch operation mechanism of the tail speed reducer through a flange, a piston rod of the tail propeller pitch operation oil cylinder is connected with one end of a tail propeller pitch operation rod through a movable joint, the other end of the tail propeller pitch operation rod is connected with a tail propeller pitch operation loading pressure rod, the tail propeller pitch operation loading pressure rod penetrates through a hollow comprehensive loading process shaft, the other end of the tail propeller pitch operation loading pressure rod is connected with a piston rod of a tail propeller pitch operation loading oil cylinder fixed at the top end of a comprehensive loading box body through a movable joint, an axial linear bearing is arranged between the tail propeller pitch operation loading pressure rod and the comprehensive loading process shaft, the tail propeller pitch operation loading pressure rod and the comprehensive loading process shaft run synchronously and can perform axial displacement adjustment at the same time, a pressure sensor is arranged on the tail propeller pitch operation oil cylinder, and the;
the tail rotor comprehensive loading hydraulic system is used for hydraulic operation control of a tail rotor shaft comprehensive loading system and a tail rotor pitch operating shaft loading system;
the test electric power loading system comprises a loading motor, a torque protector, a rzeppa universal coupling, a bearing seat, a first bevel gear and a second bevel gear; the loading motor and the comprehensive loading process shaft are installed at 90 degrees horizontally, 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 universal coupler, the shaft end of the first bevel gear is installed on a bearing seat, a second bevel gear is installed on the comprehensive loading process shaft and is meshed with the first bevel gear, the loading motor generates electricity and applies work to load, and the generated current is provided for the 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.
2. The combined test bed for the mid-tail speed reducer and the tail-tail speed reducer of the helicopter according to claim 1, characterized in that: the anti-vibration test bed is characterized by further comprising a mounting base and a test flat plate, wherein the mounting base is integrally cast by reinforced concrete, anti-vibration grooves are formed in the periphery of the mounting base, damping materials are filled in the anti-vibration grooves, the test flat plate is fixedly mounted on the mounting base through the adjustment effect of a three-wedge anti-vibration adjusting sizing block, and the mounting base is fixed on the test flat plate.
3. The combined test bed for the mid-tail speed reducer and the tail-tail speed reducer of the helicopter according to claim 1, characterized in that: the exposed part of the transmission piece is provided with a safety shield.
4. The helicopter mid and tail speed reducer comprehensive test bed of claim 3, characterized in that: the safety shield comprises a steel skeleton, a porous inner and outer sleeve plate, sound-absorbing and sound-insulating cotton and a stainless steel outer protective plate.
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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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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112478195A (en) * | 2020-11-20 | 2021-03-12 | 中国直升机设计研究所 | Helicopter comprehensive test method |
| CN114955001A (en) * | 2022-06-17 | 2022-08-30 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
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| CN112478195A (en) * | 2020-11-20 | 2021-03-12 | 中国直升机设计研究所 | Helicopter comprehensive test method |
| CN112478195B (en) * | 2020-11-20 | 2022-09-16 | 中国直升机设计研究所 | Helicopter comprehensive test method |
| CN114955001A (en) * | 2022-06-17 | 2022-08-30 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
| CN114955001B (en) * | 2022-06-17 | 2024-05-31 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
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| CN111879511B (en) | 2024-05-28 |
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