CN205593747U - Helicopter main reducer rotor loading device based on hydraulic pressure loading - Google Patents
Helicopter main reducer rotor loading device based on hydraulic pressure loading Download PDFInfo
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- CN205593747U CN205593747U CN201620421724.8U CN201620421724U CN205593747U CN 205593747 U CN205593747 U CN 205593747U CN 201620421724 U CN201620421724 U CN 201620421724U CN 205593747 U CN205593747 U CN 205593747U
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- hydraulic
- loading disc
- main reducer
- loading
- rotor shaft
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Abstract
The utility model provides a helicopter main reducer rotor loading device based on hydraulic pressure loading, includes loading disc, axial hydraulic pressure loading jar, magnetic brake, antifriction bearing, radial hydraulic pressure loading jar, this loading disc cover is located antifriction bearing and is gone up and is connected with rotor shaft, and axial hydraulic pressure load jar is equipped with five and be 72 axial evenly distributed planes on the loading disc according to the angle that differs, and radially the hydraulic pressure load is equipped with two and be 90 radial distribution face of cylinder outside the loading disc according to the angle that differs, and the magnetic brake sets up the rotation that is used for controlling rotor shaft in rotor shaft's tip, it can effectively simulate helicopter main reducer's under the various operating modes equitable true load, provides the scientific basis for assay main reducer's load characteristic and vibration characteristic to overall structure scientific and reasonable, the simple installation, low in manufacturing cost, market prospect is wide, convenient to popularize and use, it extensively is applicable to helicopter main reducer's simulation failure analysis, healthy maintaining method and tactics research.
Description
Technical field
This utility model relates to Helicopter Technology field, particularly relates to a kind of Helicopter Main Reducer based on hydraulic loaded
Rotor charger.
Background technology
Drive system is one of big critical component of helicopter three, is the unique power output part of turboshaft engine, goes straight up to
Machine performance depends greatly on the performance of drive system；Owing to helicopter flight environment is often the most severe, air-flow becomes
Changing and flight adjusts the operating mode polytropy caused and makes Helicopter Transmission System Frequent Troubles, drive system is that helicopter is easiest to
The part broken down, once breaks down and often causes major accident, directly threatens the flight safety of helicopter；Statistical table
It is bright, because, in the helicopter flight accident that mechanical breakdown causes, the accident of 68% causes due to driving unit fault, power train
The maintenance cost of system accounts for the 58% of total maintenance cost, it is seen that the safety of drive system is most important for helicopter.
Helicopter Main Reducer is one of crucial drive disk assembly of Helicopter Transmission System, and it is by engine power on demand
Pass to rotor shaft, tail-rotor, adnexa etc., be parts the most complicated, maximum, the heaviest in drive system；In flight course, flight
Operating mode is complicated and changeable, and blade will produce torque load, lift and bending load, and pass to main reducing gear, to main reducing gear band
Carry out dynamic response complicated and changeable, and prior art is difficult to simulate Helicopter Main Reducer under complex working condition and the most reasonably carries
Lotus, brings difficulty to correlational study.
Summary of the invention
For above-mentioned situation, the purpose of this utility model is to provide a kind of Helicopter Main Reducer based on hydraulic loaded
Rotor charger, it uses and loading disc is arranged axially and radially hydraulic loaded cylinder, can effectively simulate under various operating mode and go straight up to
The reasonable real load of owner's decelerator, provides scientific basis for the load character and vibration characteristics analyzing main reducing gear, it is achieved
Drive system safe and highly efficient operation.
For realizing above-mentioned task, a kind of Helicopter Main Reducer rotor charger based on hydraulic loaded, including loading
Dish, axial hydraulic load cylinder, magnetic brake, rolling bearing, hydraulic radial loading cylinder；Described loading disc is through rolling bearing and rotation
Wing axle connects, and described axial hydraulic loads cylinder and is arranged at plane on loading disc, and described hydraulic radial loads cylinder and is arranged at loading disc
External cylindrical surface, described magnetic brake is arranged at the end of rotor shaft for controlling the rotation of rotor shaft.
For realizing this utility model structure, effect optimization, its further step: described loading disc is sheathed on rolling bearing
Outer ring, this rolling bearing inner ring is sheathed in rotor shaft.
The Internal and external cycle of described rolling bearing uses interference to be equipped with rotor shaft, loading disc respectively.
Described magnetic brake is arranged at the rotor shaft end above loading disc.
Described axial hydraulic loads cylinder and is provided with five, and is 72 ° by difference angle and is axially uniformly distributed on loading disc flat
Face.
Described hydraulic radial loads cylinder and is provided with two, and is that 90 ° of radial distribution are in loading disc external cylindrical surface by difference angle.
Described axial hydraulic loads cylinder and is uniformly distributed in the periphery of planar central on loading disc.
This utility model provides a kind of Helicopter Main Reducer rotor charger based on hydraulic loaded, including loading
Dish, axial hydraulic load cylinder, magnetic brake, rolling bearing, hydraulic radial loading cylinder；Described loading disc is sheathed on rolling bearing
Upper and is connected with rotor shaft, described axial hydraulic loading cylinder is provided with five and is 72 ° by difference angle and is axially uniformly distributed in and adds
Plane on load plate, described hydraulic radial loading cylinder is provided with two and is that 90 ° of radial distribution are in loading disc outside cylinder by difference angle
Face, described magnetic brake is arranged at the end of rotor shaft for controlling the technical scheme of the rotation of rotor shaft；It uses adding
Load plate arranges axially and radially hydraulic loaded cylinder, can effectively simulate the truest of Helicopter Main Reducer under various operating mode and carry
Lotus, for analyzing load character and the vibration characteristics of main reducing gear, it is ensured that drive system safe and highly efficient operation provides scientific basis, and
And overall structure is scientific and reasonable, simple installation, low cost of manufacture, wide market, it is simple to promote the use of.
This utility model produced beneficial effect compared to existing technology:
I, this utility model uses and arranges loading disc in rotor shaft, and is respectively provided with axial hydraulic loading cylinder and radial direction liquid
Pressure loads cylinder, it is achieved thereby that Helicopter Main Reducer axle power and the comprehensive loading of moment of flexure, is conducive to analyzing under various operating mode straight
Rise owner's decelerator load character, be conducive to carrying out the research of main reducing gear vibration-testing；
II, this utility model uses and arranges magnetic brake in rotor shaft, it is achieved that Helicopter Main Reducer moment of torsion
Load, be conducive to analyzing Helicopter Main Reducer load character under various operating mode, be conducive to carrying out main reducing gear vibration-testing and grind
Study carefully；
III, this utility model is easy to more fully carry out the failure evolution mechanism of Helicopter Main Reducer, signal characteristic carries
Access method, Incipient Fault Diagnosis method, health maintenance method and strategy study；
IV, this utility model can effectively simulate the reasonable real load of Helicopter Main Reducer under various operating mode, for analyzing
The load character of main reducing gear and vibration characteristics, it is ensured that drive system safe and highly efficient operation provides scientific basis, and overall knot
Structure is scientific and reasonable, simple installation, low cost of manufacture, has significant economic benefit and social benefit, wide market, it is simple to
Promote the use of.
This utility model is applicable to the simulated failure analysis of Helicopter Main Reducer, health maintenance method and strategy study.
Below with reference to figure, this utility model is described in further detail.
Accompanying drawing explanation
Fig. 1 is this utility model integral installation structural front view.
Fig. 2 is this utility model integral installation structure top view.
Fig. 3 is overall structure front view of the present utility model.
In figure: 1-loading disc, 2-axial hydraulic loads cylinder, 3-magnetic brake, 4-rolling bearing, and 5-hydraulic radial loads
Cylinder, 6-rotor shaft, 7-main reducing gear, 8-converter, 9-gear mechanism, 10-drives motor.
Detailed description of the invention
Referring to the drawings, operation principle of the present utility model: controlled the rotation of rotor shaft 6 by magnetic brake 3, can simulate
Moment of torsion suffered by rotor shaft 6 in-flight；And its loading disc 1 is connected with rotor shaft 6 through rolling bearing 4, and by five axially
Hydraulic loaded cylinder 2 loads axial force, and helicopter simulating axial stress suffered by rotor shaft 6 in-flight, two hydraulic radials add
Carrying cylinder 5 and load radial force, the helicopter simulating moment of flexure that rotor shaft 6 is subject to in-flight, by changing the big of different directions radial force
Little, it is possible to achieve the moment of flexure of all directions loads；Described axial hydraulic load cylinder 2 and hydraulic radial load cylinder 5 respectively with hydraulic pressure
Control system connects, and this hydraulic control system provides high pressure fuel source for loading cylinder 5 for axial hydraulic loading cylinder 2 and hydraulic radial
And control the output of oil cylinder power.
By the statistical data of certain type helicopter flight loading spectrum existing, can be calculated this rotor charger should add
The magnitude of load carried；Such as: by inquiring about the statistical data of certain similar type flight load spectrum, obtaining load data is rotor shaft
Axial force FM=17140N, rotor shaft moment M=10477N m, rotor shaft moment of torsion Me=4722N m；
Each axial hydraulic loads cylinder and answers the size of loading force to be: Fi=FM(n is axial liquid to/n=17410/5=3482N
Pressure loads cylinder number)；Can be thus 18mm according to hydraulic loaded cylinder type selecting reference selector footpath, cylinder diameter be the hydraulic loaded of 32mm
Cylinder, its loading range is thrust 6KN, pressure 4KN.
Hydraulic radial loads cylinder and answers the size of loading force to be respectively Fx、Fy, it makes a concerted effort to beBy calculation of Bending Moment
Formula M=F × L can get the size of making a concerted effort that two hydraulic loaded cylinders should load and is about: F=M/L=10477/1.1=9525N
(L is main reducing gear rotor shaft length)；Being 25mm according to hydraulic loaded cylinder type selecting reference selector footpath, cylinder diameter is the hydraulic pressure of 50mm
Loading cylinder, and Fx、FyOnly need to ensure that size is constant with joint efforts, himself big I changes, thus realizes adding of different directions moment of flexure
Carry；And load the magnetic brake used in moment of torsion, then according to rotor shaft moment of torsion MeSize choose suitable model.
As it is shown on figure 3, loading disc 1 of the present utility model is sheathed on rolling bearing 4 and is connected with rotor shaft 6, described rolling
The Internal and external cycle of dynamic bearing 4 uses interference to be equipped with respectively with rotor shaft 6, loading disc 1；Described magnetic brake 3 is arranged at loading disc 1
Top and be connected to control the rotation of rotor shaft 6 with the end of rotor shaft 6；Described axial hydraulic loads cylinder 2 and is provided with five,
And be 72 ° by difference angle and be axially uniformly distributed in plane on loading disc 1, this axial hydraulic loads cylinder 2 axle with loading disc 1
Being that the center of circle is uniformly distributed in plane periphery on loading disc 1 to center, described hydraulic radial loads cylinder 5 and is provided with two, and by difference
Angle is that 90 ° of radial distribution are in loading disc 1 external cylindrical surface.
As depicted in figs. 1 and 2, what Helicopter Main Reducer vibration characteristics experiment porch was loaded by this utility model is concrete real
Applying method is as follows:
Step one: start two driving motors 10, two driving motors 10 use two high-performance vector frequency converters 8 to control
System, it is ensured that the power of two driving motors 10 is identical with rotating speed；The power driving motor 10 passes to main subtracting by gear mechanism 9
Speed device 7, drives rotor shaft 6, caudal wing shaft and other adnexaes to rotate；The rotating speed of rotor shaft 6 can be according to rotating speed under different flight operating modes
Difference by converter 8 Terminal control；
Step 2: then utilize this utility model helicopter simulating main reducing gear 7 load subjected to, according to different flight
Operating mode, the load under the different situations such as helicopter simulating flies front, rises, side flies；Loaded by five axial hydraulic during simulation
Cylinder 2 applies axial force, and five axial hydraulic load cylinder 2 and work the power of applied equal size simultaneously；Again by two or
Three hydraulic radials load cylinder 5 and apply radial force, the moment of flexure that simulation rotor shaft 6 is subject to, and execute by changing hydraulic radial loading cylinder 5
The size of power, the moment of flexure that can realize all directions loads；Drive magnetic brake 3 to work, apply with it, to rotor shaft 6, the side of rotation
To contrary frictional force, the moment of torsion that rotor shaft 6 is subject to can be simulated；Each hydraulic loaded cylinder is controlled by hydraulic control system, and
Applied to provide high pressure fuel source for load by hydraulic power unit.
The foregoing is only preferred embodiment of the present utility model, be not limited to this utility model, for this
For the technical staff in field, this utility model can have various modifications and variations；All in spirit of the present utility model and principle
Within, any modification, equivalent substitution and improvement etc. made, within should be included in protection domain of the present utility model.
Claims (7)
1. a Helicopter Main Reducer rotor charger based on hydraulic loaded, it is characterised in that include loading disc, axially
Hydraulic loaded cylinder, magnetic brake, rolling bearing, hydraulic radial load cylinder；Described loading disc is through rolling bearing with rotor shaft even
Connecing, described axial hydraulic loads cylinder and is arranged at plane on loading disc, and described hydraulic radial loads cylinder and is arranged at loading disc outside cylinder
Face, described magnetic brake is arranged at the end of rotor shaft for controlling the rotation of rotor shaft.
A kind of Helicopter Main Reducer rotor charger based on hydraulic loaded the most according to claim 1, its feature
Being that described loading disc is sheathed on housing washer, this rolling bearing inner ring is sheathed in rotor shaft.
A kind of Helicopter Main Reducer rotor charger based on hydraulic loaded the most according to claim 2, its feature
It is that the Internal and external cycle of described rolling bearing uses interference to be equipped with rotor shaft, loading disc respectively.
A kind of Helicopter Main Reducer rotor charger based on hydraulic loaded the most according to claim 1, its feature
It is that described magnetic brake is arranged at the rotor shaft end above loading disc.
A kind of Helicopter Main Reducer rotor charger based on hydraulic loaded the most according to claim 1, its feature
It is that described axial hydraulic loads cylinder and is provided with five, and is 72 ° by difference angle and is axially uniformly distributed in plane on loading disc.
A kind of Helicopter Main Reducer rotor charger based on hydraulic loaded the most according to claim 1, its feature
It is that described hydraulic radial loads cylinder and is provided with two, and is that 90 ° of radial distribution are in loading disc external cylindrical surface by difference angle.
A kind of Helicopter Main Reducer rotor charger based on hydraulic loaded the most according to claim 5, its feature
It is that described axial hydraulic loads cylinder and is uniformly distributed in the periphery of planar central on loading disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620421724.8U CN205593747U (en) | 2016-05-11 | 2016-05-11 | Helicopter main reducer rotor loading device based on hydraulic pressure loading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620421724.8U CN205593747U (en) | 2016-05-11 | 2016-05-11 | Helicopter main reducer rotor loading device based on hydraulic pressure loading |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205593747U true CN205593747U (en) | 2016-09-21 |
Family
ID=56930557
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620421724.8U Expired - Fee Related CN205593747U (en) | 2016-05-11 | 2016-05-11 | Helicopter main reducer rotor loading device based on hydraulic pressure loading |
Country Status (1)
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|---|---|
| CN (1) | CN205593747U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| 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 |
| CN110132589A (en) * | 2019-06-14 | 2019-08-16 | 哈工大机器人（合肥）国际创新研究院 | A kind of testing stand in moment of flexure adjustable test speed reducer service life |
| CN111307447A (en) * | 2019-11-29 | 2020-06-19 | 重庆大学 | Bending rigidity testing system for parallel shaft output speed reducer |
| CN111855201A (en) * | 2020-09-01 | 2020-10-30 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN113533085A (en) * | 2021-07-01 | 2021-10-22 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
-
2016
- 2016-05-11 CN CN201620421724.8U patent/CN205593747U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| 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 |
| CN110132589A (en) * | 2019-06-14 | 2019-08-16 | 哈工大机器人（合肥）国际创新研究院 | A kind of testing stand in moment of flexure adjustable test speed reducer service life |
| CN110132589B (en) * | 2019-06-14 | 2024-05-17 | 安徽哈工湛庐科技装备有限公司 | Test bench for testing service life of speed reducer with adjustable bending moment |
| CN111307447A (en) * | 2019-11-29 | 2020-06-19 | 重庆大学 | Bending rigidity testing system for parallel shaft output speed reducer |
| CN111855201A (en) * | 2020-09-01 | 2020-10-30 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN111855201B (en) * | 2020-09-01 | 2022-03-22 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN113533085A (en) * | 2021-07-01 | 2021-10-22 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
| CN113533085B (en) * | 2021-07-01 | 2023-03-28 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160921 Termination date: 20190511 |