CN202853893U - Device for testing coaxial contrarotating rotor wings of helicopter - Google Patents
Device for testing coaxial contrarotating rotor wings of helicopter Download PDFInfo
- Publication number
- CN202853893U CN202853893U CN 201220547116 CN201220547116U CN202853893U CN 202853893 U CN202853893 U CN 202853893U CN 201220547116 CN201220547116 CN 201220547116 CN 201220547116 U CN201220547116 U CN 201220547116U CN 202853893 U CN202853893 U CN 202853893U
- Authority
- CN
- China
- Prior art keywords
- shaft
- transmission
- helicopter
- rotor
- outer shaft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
The utility model relates to a device for testing coaxial contrarotating rotor wings of a helicopter, wherein a motor is mounted on a base and connected with an inner shaft speed changer and an outer shaft speed changer in series, the output end of the inner shaft speed changer is connected with the inner shafts of the rotor wings, the output end of the outer shaft speed changer is connected with the outer shafts of the rotor wings, the inner shafts and the outer shafts are mounted on an inner shaft bearing seat, an inner shaft coupling and an outer shaft coupling are respectively equipped with a torquemeter, and the bearing seat is equipped with a torque balance. The device for testing the coaxial contrarotating rotor wings of a helicopter breaks through a thinking set that the speed changer in a rotor wing test must be an integrated gear case, can realize the performance and reliability test of the coaxial contrarotating rotor wings through two gear cases with the functions related and the structures independent, and can simultaneously measure the dynamic lifting force, torque and bending moment data of two sets of rotor wings respectively.
Description
Technical field
The utility model relates to a kind of lifting airscrew test unit, the coaxial counter-rotating Rotor Test of especially a kind of helicopter device.
Background technology
The lifting airscrew technology is one of development core technology of helicopter, and its experimental technique is gordian technique wherein.The lifting airscrew test needs to measure the projects such as dynamic lift, moment of flexure, moment of torsion.Traditional lifting airscrew measurement mechanism can only be measured rotor lift, moment of flexure, the moment of torsion of single rotation at present.Contrarotation bispin wing technology is to adopt two groups of rotating speeds identical at same axis, the technology of switched in opposite rotor, two groups of rotors are connected on the coaxial interior axle and outer shaft, the reactive torque of cancelling each other, thereby can cancel tail-rotor, shorten fuselage length, reduce fuselage weight, it is one of new developing direction of helicopter, but this technology has proposed very high requirement to Rotor Test, for example be limited to the narrow space between the interior outer shaft, interacting and the structural limitations of conventional speed reduction unit of measuring equipment is difficult to measure respectively simultaneously the lift that two groups of rotors produce on inside and outside two axles of contrarotation, moment of flexure, the data such as moment of torsion.At present, domesticly there is no the testing equipment of contrarotation rotor and can't finish the test of this rotor.The testing program that proposes at present all can only be measured comprehensive lift and the moment of flexure after the bispin wing combines, performance and response characteristic that can not each rotor of Efficient Evaluation.
Summary of the invention
The purpose of this utility model provides a kind of measurement contrarotation bispin wing lift that each rotor produces, moment of torsion and moment of flexure characteristic, the testing equipment with high feasibility and reliability.
The technical solution of the utility model is, test unit comprises motor, interior shaft transmission, outer shaft transmission, interior axle shaft coupling, the outer shaft shaft coupling, motor is installed on the pedestal and by coupling shaft and is in series with interior shaft transmission and outer shaft transmission, the output terminal of described interior shaft transmission links to each other with the interior axle of rotor by interior axle shaft coupling, the output terminal of outer shaft transmission links to each other with the outer shaft of rotor by the outer shaft shaft coupling, the switched in opposite of the output terminal of described interior shaft transmission and outer shaft transmission, described interior axle is installed on the inner shaft bearing seat by inner shaft bearing, outer shaft is installed on the outer bearing housing by outer axle bearing, on described interior axle shaft coupling and the outer shaft shaft coupling torquer is installed all, be connected with an end of torsion balance on inner shaft bearing seat and the outer bearing housing, the other end of described torsion balance is fixedly connected with pedestal.
Described interior shaft transmission and outer shaft transmission adopt spur gear transmission chain transmission or the transmission of Helical gear Transmission chain; Described interior axle shaft coupling and outer shaft shaft coupling are installed in respectively the inside of torsion balance; The bearing of installing in the described outer bearing housing is a pair of taper roller bearing.
In use, the lift of rotor and moment of flexure pass to torsion balance by inner shaft bearing seat and outer bearing housing respectively, calculate lift and moment by the stressed result of torsion balance rod member is measured with decoupling zero; The moment of torsion of rotor passes to torquer by interior axle shaft coupling and outer shaft shaft coupling, and measurement and decoupling zero by torquer calculate torque value.
In the utility model, the variator of having broken through Rotor Test must be a thinking set that the gear case that integrates is such, but variator develops into independently gear case of 2 function association structures because of needs, for 2 groups of torsion balance, moments of torsion of measuring respectively inside and outside rotor data are taken into account shaft coupling and bearing seat provides installing space.In limited space structure, solve the measurement difficult problem of 2 contrarotation rotor moments of torsion, moment of flexure and lift.Shaft coupling can avoid the moment of flexure of axle that the torquer measurement result is exerted an influence.2 variators adopt spur gear or Helical gear Transmission chain according to rotor load and test noise requirements, satisfy the rotating speed such as inside and outside rotor contrarotation by the allotment number of teeth or do not wait the requirement of rotating speed.Between 2 variators by coupling shaft realize the two rotating speed synchronously, have simple in structure, service-strong characteristics.Outer bearing housing adopts a pair of taper roller bearing positioned opposite, reaches good support stiffness with very short axial space, thereby and then the length that reduces interior axle increase in shaft rigidity.Moment of torsion is taken into account shaft coupling and is installed in torsion balance inside, can take full advantage of the torsion balance inner space, reduces the experimental provision axial dimension, shaft rigidity in increasing.This device can be realized the Performance And Reliability test of contrarotation rotor, can measure respectively simultaneously lift, moment of torsion and the moment of flexure dynamic data of two groups of rotors.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
As shown in the figure, the coaxial counter-rotating Rotor Test of helicopter device comprises motor 1, interior shaft transmission 3, outer shaft transmission 6, interior axle shaft coupling 17, outer shaft shaft coupling 8, motor 1 is installed on the pedestal 2 and by coupling shaft 5 and is in series with interior shaft transmission 3 and outer shaft transmission 6, the output terminal of described interior shaft transmission 3 links to each other with the interior axle 10 of rotor by interior axle shaft coupling 17, the output terminal of outer shaft transmission 6 links to each other with the outer shaft 13 of rotor by outer shaft shaft coupling 8, the switched in opposite of the output terminal of described interior shaft transmission 3 and outer shaft transmission 6, described interior axle 10 is installed on the inner shaft bearing seat 15 by inner shaft bearing, outer shaft 13 is installed on the outer bearing housing 9 by outer axle bearing, on described interior axle shaft coupling 17 and the outer shaft shaft coupling 8 torquer is installed all, be connected with an end of torsion balance on inner shaft bearing seat 15 and the outer bearing housing 9, the other end of described torsion balance and pedestal 2 are fixing.The interior shaft transmission 3 of stating and outer shaft transmission 6 adopt spur gear transmission chain transmission or the transmission of Helical gear Transmission chain; Described interior axle shaft coupling 17 and outer shaft shaft coupling 8 are installed in respectively the inside of torsion balance; The bearing of described outer bearing housing 9 interior installations is a pair of taper roller bearing.
Claims (5)
1. helicopter contrarotation Rotor Test device, it is characterized in that, described device comprises motor (1), interior shaft transmission (3), outer shaft transmission (6), interior axle shaft coupling (17), outer shaft shaft coupling (8), motor (1) is installed in pedestal (2) and upward and by coupling shaft (5) is in series with interior shaft transmission (3) and outer shaft transmission (6), the output terminal of described interior shaft transmission (3) links to each other with the interior axle (10) of rotor by interior axle shaft coupling (17), the output terminal of outer shaft transmission (6) links to each other with the outer shaft (13) of rotor by outer shaft shaft coupling (8), the switched in opposite of the output terminal of described interior shaft transmission (3) and outer shaft transmission (6), described interior axle (10) is installed on the inner shaft bearing seat (15) by inner shaft bearing, outer shaft (13) is installed on the outer bearing housing (9) by outer axle bearing, on described interior axle shaft coupling (17) and the outer shaft shaft coupling (8) torquer is installed all, inner shaft bearing seat (15) is connected with an end of torsion balance with outer bearing housing (9) is upper, and the other end of described torsion balance is fixedly connected with pedestal (2).
2. helicopter contrarotation Rotor Test device as claimed in claim 1 is characterized in that, described interior shaft transmission (3) and outer shaft transmission (6) adopt the transmission of spur gear transmission chain.
3. helicopter contrarotation Rotor Test device as claimed in claim 1 is characterized in that, described interior shaft transmission (3) and outer shaft transmission (6) adopt the transmission of Helical gear Transmission chain.
4. helicopter contrarotation Rotor Test device as claimed in claim 1 is characterized in that, described interior axle shaft coupling (17) and outer shaft shaft coupling (8) are installed in respectively the inside of torsion balance.
5. helicopter contrarotation Rotor Test device as claimed in claim 1 is characterized in that, the bearing of installing in the described outer bearing housing (9) is a pair of taper roller bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220547116 CN202853893U (en) | 2012-10-24 | 2012-10-24 | Device for testing coaxial contrarotating rotor wings of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220547116 CN202853893U (en) | 2012-10-24 | 2012-10-24 | Device for testing coaxial contrarotating rotor wings of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202853893U true CN202853893U (en) | 2013-04-03 |
Family
ID=47985077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220547116 Expired - Fee Related CN202853893U (en) | 2012-10-24 | 2012-10-24 | Device for testing coaxial contrarotating rotor wings of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202853893U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN110562483A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN111532450A (en) * | 2020-04-30 | 2020-08-14 | 中国航发哈尔滨东安发动机有限公司 | Mechanical closed transmission device for main reducing test bed of coaxial double-propeller helicopter |
-
2012
- 2012-10-24 CN CN 201220547116 patent/CN202853893U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN105547676B (en) * | 2015-12-25 | 2018-01-12 | 北京航空航天大学 | A kind of arm-type rotor model.test system of multifunctional rotary |
| CN110562483A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN110562483B (en) * | 2019-09-24 | 2022-07-15 | 哈尔滨工业大学 | Lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN111532450A (en) * | 2020-04-30 | 2020-08-14 | 中国航发哈尔滨东安发动机有限公司 | Mechanical closed transmission device for main reducing test bed of coaxial double-propeller helicopter |
| CN111532450B (en) * | 2020-04-30 | 2023-09-15 | 中国航发哈尔滨东安发动机有限公司 | Mechanical closed transmission device for main test-reducing platform of coaxial double-oar helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102901623A (en) | Device for testing coaxial inversion rotor wing of helicopter | |
| CN202853893U (en) | Device for testing coaxial contrarotating rotor wings of helicopter | |
| CN104316229B (en) | A kind of screw propeller dynamic tension and moment of torsion duplex measurement device | |
| CN107884185B (en) | Single-stage double helical tooth planetary drive dynamics features Testbed | |
| KR100913667B1 (en) | Helicopter Tail Rotor Test Rig | |
| CN101509814B (en) | Design method of miniature bearing dynamic friction moment measurement instrument | |
| CN110844113B (en) | Rigid coaxial dual-rotor test bed capable of simultaneously measuring upper rotor load and lower rotor load | |
| CN203037441U (en) | Single-component rod low-speed hinge moment measuring device | |
| CN102879138A (en) | Motor moment testing tool | |
| CN104122093A (en) | Electric actuator elastic torque loading device | |
| CN103969021B (en) | Properller thrust and torque measurement balance | |
| CN108918136B (en) | Propeller dynamic tension and torsion measuring device | |
| CN102156047A (en) | Loading simulation device for test bed of wind turbine | |
| CN104165726A (en) | Calibration device for dynamometer | |
| CN103217138A (en) | Bevel gear assembly gap measuring device | |
| CN102678832B (en) | Double output and self-balance planetary reducer | |
| CN105021337A (en) | Propeller driving rotation force measuring apparatus and force measuring method | |
| CN104849009B (en) | Two-stage fixed axis gear transmission mechanism vibration testing device | |
| CN105203293A (en) | Dummy air-drop six-component balance test system and method | |
| CN102818693A (en) | Half-module pivoted window mechanism applied to sub transonic speed wind tunnel | |
| CN202281693U (en) | Drive axle load test-bed | |
| CN201285334Y (en) | Measurement instrument for detecting dynamic friction torque of bearing | |
| CN102607750B (en) | Test-bed for friction torque of rolling bearing | |
| CN201882837U (en) | Transmission device of load sharing type rack and pinion construction lifter | |
| CN109655270B (en) | Device capable of measuring torque at high rotating speed by cantilever installation |
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: 20130403 Termination date: 20171024 |