CN101614615B - Simulative loader of tail reducer of helicopter - Google Patents
Simulative loader of tail reducer of helicopter Download PDFInfo
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- CN101614615B CN101614615B CN2009103039958A CN200910303995A CN101614615B CN 101614615 B CN101614615 B CN 101614615B CN 2009103039958 A CN2009103039958 A CN 2009103039958A CN 200910303995 A CN200910303995 A CN 200910303995A CN 101614615 B CN101614615 B CN 101614615B
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Abstract
The invention relates to a simulative loader of a tail reducer of a helicopter, which consists of a tail reducer, a tail-deceleration tail rotor shaft, a flange, an aerodynamic load equivalent acting surface, a force sensor, a loading shaft and a reverse box, and is characterized in that: the tail-deceleration tail rotor shaft with the tail reducer is connected with the loading shaft; the loading shaft is provided with a loading bearing with a loading bearing block; the loading bearing block is provided with two axial oil cylinders parallel to the loading shaft and a radial oil cylinder vertical to the loading shaft. The simulative loader is simple in structure, convenient in installation and good in experiment effect, avoids influencing the dynamic behavior of the tail reducer and causing disadvantageous additional vibration to the tested tail reducer, and can apply all aerodynamic load of a tail rotor onto the tail reducer.
Description
Technical field
The present invention relates to a kind of experimental provision, be specifically related to tail reducer of helicopter tail-rotor aerodynamic loading simulative loader.
Background technology
Tail reducer of helicopter is used to drive the tail-rotor rotation of helicopter, the torque that makes the fuselage rotation that produces when working with the balancing helicopter main rotor.When tail reducer is worked on helicopter, except transmitting rotating speed, moment of torsion, also bear the aerodynamic loading that the tail-rotor rotation produces, comprise tail-rotor axial force, moment of flexure and shearing, this aerodynamic loading general action is subtracting the propeller hub center (being aerodynamic loading loading face) that output tail-rotor flange is connected with tail.
For design, processing and the matching requirements of satisfying tail reducer, tail reducer can reliably, steady, lasting be worked on helicopter, need by a large amount of ground experiments usually.When carrying out ground experiment,, must simulate the loaded-up condition of tail reducer as far as possible exactly for warranty test real result, reliable.This just needs a kind of simulative loader to realize the torque load experiment that tail reducer transmits.
Summary of the invention
The purpose of this invention is to provide a kind of simple in structure, easy for installation, the simulative loader of tail reducer of helicopter that experiment effect is good.
The present invention is by tail reducer, and tail subtracts tail-rotor axle, flange, aerodynamic loading equivalent action face, force transducer loads axle, reverse box is formed, and it is characterized in that: the tail of described magnetic tape trailer speed reduction unit subtracts the tail-rotor axle and is connected with the loading axle, loads the load bearings that axle is provided with band load bearings seat; Described load bearings seat is provided with two axial oil cylinders parallel with loading axle, a radial oil cylinders vertical with loading axle.
Also be connected with guide rail on the described load bearings seat, the load bearings seat can move along loading axle horizontal.
The present invention is simple in structure, and is easy for installation, and experiment effect is good.Do not influence the dynamics of tail reducer, produce disadvantageous extraneous vibration can for tested tail reducer yet, whole aerodynamic loadings of tail-rotor can be applied on the tail reducer.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Among Fig. 1: 1, tail reducer, 2, tail subtracts the tail-rotor axle, 3, flange, 4 aerodynamic loading equivalent action faces, 5, axial oil cylinder, 6, force transducer, 7, the load bearings seat, 8, load bearings, 9, load axle, 10, reverse box, 11, Hooks coupling universal coupling, 12, guide rail, 13, radial oil cylinders.
Embodiment
As seen from Figure 1, rotating speed, torque according to the tail reducer transmission, and the equivalent action face of the size of the axial force in the aerodynamic loading, moment of flexure and shearing and aerodynamic loading, by tail reducer 1, tail subtracts tail-rotor axle 2, flange 3, aerodynamic loading equivalent action face 4, force transducer 6 loads axle 9, the simulative loader of tail reducer of helicopter that reverse box 10 is formed, aerodynamic loading equivalent action face 4 is 74mm apart from the end face D of flange 3.The tail of tail reducer 1 subtracts tail-rotor axle 2 and loads axle 9 and is connected by flange 3, and the tail that the load that assurance is applied to aerodynamic loading equivalent action face 4 can be delivered to tail reducer 1 subtracts on the tail-rotor axle 2.Load axle 9 and be provided with the load bearings 8 of being with load bearings seat 7, load bearings seat 7 is provided with two axial oil cylinders 5 parallel with loading axle 9, a radial oil cylinders 13 vertical with loading axle 9, the compound action by these three oil cylinder power produces the simulation load that acts on the load equivalent face.Load axle 9 tails and subtract 2 rotations of tail-rotor axle with tail reducer 1, axially oil cylinder 5, radial oil cylinders 13 do not rotate, the loading transfer between the loading axle 9 of realizing rotation by load bearings seat 7 and load bearings 8 and non-rotary axial oil cylinder 5, the radial oil cylinders 13 be connected.
After tail reducer 1 is subjected to the aerodynamic loading effect, tail subtracts the flexural deformation in the tail-rotor axle 2 meeting generating technique scopes, casing also can produce certain deformation, also be connected with guide rail 12 on the load bearings seat 7 for this reason, load bearings seat 7 can move freely along loading axle 9 horizontal directions, the normal deformation of tail reducer is not produced interference to guarantee loader.
Subtracting the right alignment of tail-rotor axle 2 for increase loading axle 9 and tail, being connected with axial telescopic Hooks coupling universal coupling 11 loading between axle 9 and the reverse box 10.
Two axial oil cylinders 5 are 190-210mm apart from the radial distance L that loads axle 9, and radial oil cylinders 13 is 175-195mm apart from load equivalent action face apart from B.
Claims (3)
1. simulative loader of tail reducer of helicopter, by tail reducer (1), tail subtracts tail-rotor axle (2), flange (3), aerodynamic loading equivalent action face (4), force transducer (6), load axle (9), reverse box (10) is formed, and it is characterized in that: the tail of described magnetic tape trailer speed reduction unit (1) subtracts tail-rotor axle (2) and is connected by flange (3) with loading spool (9), loads the load bearings (8) that axle (9) is provided with band load bearings seat (7); Described load bearings seat (7) be provided with two with load axle (9) parallel axial oil cylinder (5), one with load (9) vertical radial oil cylinders (13); Described aerodynamic loading equivalent action face (4) is 74mm apart from the end face of flange (3), loads between axle (9) and the reverse box (10) to be connected with axial telescopic Hooks coupling universal coupling (11).
2. simulative loader according to claim 1 is characterized in that: also be connected with guide rail (12) on the load bearings seat (7), load bearings seat (7) can move horizontally along loading axle (9).
3. simulative loader according to claim 1 is characterized in that: described axial oil cylinder (5) is 190-210mm apart from the radial distance L that loads axle (9), and radial oil cylinders (13) is 175-195mm apart from aerodynamic loading equivalent action face (4) apart from B.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103039958A CN101614615B (en) | 2009-07-03 | 2009-07-03 | Simulative loader of tail reducer of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103039958A CN101614615B (en) | 2009-07-03 | 2009-07-03 | Simulative loader of tail reducer of helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101614615A CN101614615A (en) | 2009-12-30 |
| CN101614615B true CN101614615B (en) | 2010-09-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009103039958A Active CN101614615B (en) | 2009-07-03 | 2009-07-03 | Simulative loader of tail reducer of helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN101614615B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105445023B (en) * | 2015-11-23 | 2017-12-15 | 西安交通大学 | A kind of industrial robot joint decelerator Static State Index test platform and method of testing |
| 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 |
| 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 |
| CN111707469B (en) * | 2020-06-24 | 2022-06-14 | 中国航发中传机械有限公司 | Helicopter tail reducer control shaft force loading test device |
| CN111999056B (en) * | 2020-07-31 | 2021-10-08 | 中南大学 | Multifunctional experiment table for simulating helicopter tail transmission vibration |
| CN111879511B (en) * | 2020-08-14 | 2024-05-28 | 湘潭科达电工专用成套设备有限责任公司 | Comprehensive test bed for tail speed reducer in helicopter |
| 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 |
| CN112485108B (en) * | 2020-10-30 | 2022-09-13 | 中国直升机设计研究所 | Three-dimensional loading test device for central part of main propeller of double-elastic bearing |
| CN114112353B (en) * | 2021-11-19 | 2023-10-27 | 中国直升机设计研究所 | Helicopter full-aircraft static test tail anti-false part |
| CN114252262B (en) * | 2021-12-09 | 2023-12-08 | 中国船舶重工集团公司第七0三研究所 | Helicopter main reducer hub load simulation loading device considering balanced static dead weight |
| CN114955001B (en) * | 2022-06-17 | 2024-05-31 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
-
2009
- 2009-07-03 CN CN2009103039958A patent/CN101614615B/en active Active
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| Publication number | Publication date |
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| CN101614615A (en) | 2009-12-30 |
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