CN111707469B - Helicopter tail reducer control shaft force loading test device - Google Patents
Helicopter tail reducer control shaft force loading test device Download PDFInfo
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- CN111707469B CN111707469B CN202010590504.9A CN202010590504A CN111707469B CN 111707469 B CN111707469 B CN 111707469B CN 202010590504 A CN202010590504 A CN 202010590504A CN 111707469 B CN111707469 B CN 111707469B
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- control shaft
- oil cylinder
- piston rod
- test device
- hollow piston
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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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- 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
- G01M13/027—Test-benches with force-applying means, e.g. loading of drive shafts along several directions
Abstract
The invention discloses a force loading test device for an operating shaft of a helicopter tail reducer, which comprises a connecting flange, a servo oil cylinder, a hollow piston rod, a tension and pressure sensor and a supporting seat, wherein one end of the connecting flange is connected with a casing of the reducer, the other end of the connecting flange is connected with the servo oil cylinder, the hollow piston rod sequentially penetrates through the connecting flange and the servo oil cylinder from the casing of the reducer and is connected with the supporting seat, a through hole in the rod is formed in the hollow piston rod along the length direction, the operating shaft of the reducer extends from one end of the through hole in the rod to the other end of the operating shaft and reaches the inside of the supporting seat, the tension and pressure sensor is positioned in the supporting seat and is fixedly connected with the supporting seat, and the operating shaft of the reducer is connected with the tension and pressure sensor. The invention can accurately simulate the actual working stress state of the operating shaft and has simple structure.
Description
Technical Field
The invention belongs to the technical field of transmission test devices, mainly relates to a test device for loading a shafting force value, and particularly relates to a helicopter tail reducer control shaft force loading device.
Background
The actuating device for the force of the control shaft of the tail speed reducer of the helicopter is an accessory, namely a course booster, which acts on the control shaft to control the flight direction of the helicopter, and is only an actuating mechanism of the control shaft, so that the force of the control shaft cannot be controlled and measured, and the actuating device is not suitable for ground bench tests. Some existing helicopter tail speed reducer operating shaft force test control devices are formed by modifying course boosters, but the cost for purchasing accessories is quite high, the modification is also quite complex, and the existing helicopter tail speed reducer operating shaft force test control devices are not suitable for ground test devices; in some test devices, an oil cylinder, an electric cylinder or an air cylinder is used for transformation, and the electric cylinder is additionally provided with a driving motor, so that the mechanical structure of the electric cylinder is complex, the weight of the device is very heavy when a large load is applied, and the electric cylinder is rarely applied to the field of stand tests of tail speed reducers of helicopters; the cylinder is hardly applied due to the defects of difficult air source supply, unstable pressure, complex sealing structure and the like; the oil cylinder is widely applied due to the advantages of simple oil source supply, stable and easily controlled pressure, simple mechanical structure and the like. However, the structure of the oil cylinder is a five-door eight-door structure, which is not only related to the structure of the tested piece, but also related to the selected servo valve structure, the matching degree of the existing testing device adopting the oil cylinder and the test piece structure is very high, once the test piece structure is changed, the testing device needs to be customized again, and the application range is narrow.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a helicopter tail reducer control shaft force loading test device which can accurately simulate the actual working stress state of an operation shaft and has a simple structure.
In order to solve the technical problems, the invention adopts the following technical scheme:
a force loading test device for a control shaft of a helicopter tail speed reducer comprises a connecting flange, a servo oil cylinder, a hollow piston rod, a pulling pressure sensor and a supporting seat, wherein one end of the connecting flange is connected with a speed reducer casing, the other end of the connecting flange is connected with the servo oil cylinder, the hollow piston rod sequentially penetrates through the connecting flange and the servo oil cylinder from the speed reducer casing and is connected with the supporting seat, a rod inner through hole is formed in the hollow piston rod along the length direction, the speed reducer control shaft extends from one end of the rod inner through hole to the other end of the speed reducer control shaft and reaches the supporting seat, the pulling pressure sensor is located in the supporting seat and is fixedly connected with the supporting seat, and the speed reducer control shaft is connected with the pulling pressure sensor.
As a further improvement to the above technical solution:
the helicopter tail reducer control shaft force loading test device further comprises a limiting piece, and the limiting piece is located between the connecting flange and the hollow piston rod and used for preventing the hollow piston rod from rotating.
The helicopter tail speed reducer control shaft force loading test device further comprises a connecting threaded sleeve, and the connecting threaded sleeve is used for connecting the speed reducer control shaft with the pull pressure sensor.
The servo oil cylinder comprises an oil cylinder body, an oil cylinder front end cover and an oil cylinder rear end cover, the hollow piston rod penetrates through the oil cylinder front end cover to enter the oil cylinder body and penetrate out of the oil cylinder rear end cover, and the hollow piston rod is connected with the oil cylinder front end cover and the oil cylinder rear end cover in a sealing mode.
The connecting flange is connected with the front end cover of the oil cylinder.
And one end of the supporting seat far away from the hollow piston rod is provided with a supporting seat end cover, and the pull pressure sensor is fixedly connected with the supporting seat end cover.
The helicopter tail speed reducer control shaft force loading test device further comprises a connecting bolt, and the tension and pressure sensor is fixedly connected with the support seat end cover through the connecting bolt.
And a limiting groove for placing the limiting part is formed in the peripheral wall of the hollow piston rod.
And a cushion cover is sleeved outside the connecting bolt and is positioned between the tension and pressure sensor and the end cover of the supporting seat.
The hollow piston rod is provided with a radial plate structure on the peripheral wall, the radial plate structure is positioned in the servo oil cylinder and divides an inner cavity chamber of the servo oil cylinder into a left cavity and a right cavity, and the left cavity is arranged close to one side of the control shaft.
Compared with the prior art, the invention has the advantages that:
the invention connects the reducer casing and the servo oil cylinder through the connecting flange, can apply the stress of the control shaft on the casing, accords with the actual working stress state of the control shaft, provides a stress bearing point for the force load applied by the control shaft, connects the control shaft with the pull pressure sensor through the hollow piston rod, can complete the control and measurement of the force value and the control and measurement of the displacement of the control shaft of the tail reducer of various types of helicopters in the ground bench test, and the stress verification condition of each joint part (indirectly deducing the stress of other structures such as a thrust bearing according to the test result of the control shaft) in the control shaft system of the tail reducer, and examines the service life and the performance of the joint part.
The invention can better simulate the function of a course booster, not only can ensure that the stress point of the control shaft of the tail speed reducer is on the casing of the speed reducer, but also can greatly reduce the weight of the loading device of the control shaft of the tail speed reducer, and meanwhile, the invention can be suitable for controlling and measuring the force value under the working condition of large load and controlling and measuring the push-pull displacement of the control shaft.
Drawings
Fig. 1 is a schematic structural view of the present invention.
The reference numerals in the figures denote:
1. a steering shaft; 2. a reducer case; 3. a connecting flange; 4. a servo cylinder; 41. a cylinder body of the oil cylinder; 411. a left lumen; 412. a right lumen; 42. a front end cover of the oil cylinder; 43. a rear end cover of the oil cylinder; 5. a servo valve; 6. a hollow piston rod; 61. a rod inner through hole; 62. a limiting groove; 7. a stopper; 8. connecting a threaded sleeve; 9. a pull pressure sensor; 10. a supporting seat; 101. a support base end cover; 11. a connecting bolt; 12. a cushion cover; 13. and locking the round nut.
Detailed Description
The invention will be described in further detail below with reference to the drawings and specific examples. Unless otherwise specified, the instruments or materials employed in the present invention are commercially available.
Example 1:
as shown in fig. 1, the helicopter tail reducer control shaft force loading test device of the present embodiment includes a connecting flange 3, a servo cylinder 4, a hollow piston rod 6, a tension and pressure sensor 9, and a support seat 10, where one end of the connecting flange 3 is connected to a reducer casing 2, and the other end is connected to the servo cylinder 4, the hollow piston rod 6 sequentially passes through the connecting flange 3 and the servo cylinder 4 from the reducer casing 2 and is connected to the support seat 10, the hollow piston rod 6 is provided with a rod inner through hole 61 along the length direction, a control shaft 1 of the reducer extends from one end of the rod inner through hole 61 to the other end and reaches the inside of the support seat 10, the tension and pressure sensor 9 is located in the support seat 10 and is fixedly connected to the support seat 10, and the control shaft 1 is connected to the tension and pressure sensor 9.
The connecting flange 3 is connected between the reducer casing 2 and the servo oil cylinder 4, is a key component for connecting the servo oil cylinder 4 and the reducer casing 2 into a whole, can apply stress on the casing of the control shaft 1, accords with the actual working stress state of the control shaft, provides a stress supporting point for applying a load on the control shaft 1, can output a voltage signal when the tension pressure sensor 9 is pulled or pressed and deformed, and transmits the voltage signal to a force value instrument through a signal wire for measuring the stress of the control shaft 1 in the test process, and the hollow piston rod 6 is a key component for connecting the servo oil cylinder 4 and the control shaft 1 into a whole, and is a key component for connecting the tension pressure sensor 9 and the control shaft 1 into a whole, so that the device has the function of measuring a force value.
In this embodiment, the helicopter tail reducer control shaft force loading test device further comprises a locking round nut 13, and the hollow piston rod 6 is connected and sealed with the supporting seat 10 through the locking round nut 13.
The helicopter tail reducer control shaft force loading test device further comprises a limiting piece 7, the limiting piece 7 is located between the connecting flange 3 and the hollow piston rod 6 and used for preventing the hollow piston rod 6 from rotating, the limiting piece 7 enables the hollow piston rod 6 to only perform axial reciprocating motion and not rotate, and accuracy of axial force load testing is guaranteed, and in the embodiment, the limiting piece 7 is a flat key.
The helicopter tail speed reducer control shaft force loading test device further comprises a connecting threaded sleeve 8, and the connecting threaded sleeve 8 is used for connecting the control shaft 1 with a pulling pressure sensor 9.
The servo oil cylinder 4 comprises an oil cylinder body 41, an oil cylinder front end cover 42 and an oil cylinder rear end cover 43, a hollow piston rod 6 penetrates through the oil cylinder front end cover 42, enters the oil cylinder body 41 and penetrates out of the oil cylinder rear end cover 43, and the hollow piston rod 6 is connected with the oil cylinder front end cover 42 and the oil cylinder rear end cover 43 in a sealing mode.
The connecting flange 3 is connected with the front end cover 42 of the oil cylinder. One end of the connecting flange 3 is connected with the speed reducer casing 2 through a fixing stud on the speed reducer casing 2, the other end of the connecting flange is connected with the servo oil cylinder 4 through a connecting screw, a connecting hole between the connecting flange 3 and the speed reducer casing 2 can be drilled according to the position of the fixing stud on the speed reducer casing 2 so as to meet the installation requirements of the same set of force loading device on different structural test pieces, a supporting seat end cover 101 is arranged at one end of the supporting seat 10 far away from the hollow piston rod 6, and the pull pressure sensor 9 is fixedly connected with the supporting seat end cover 101.
The helicopter tail speed reducer control shaft force loading test device further comprises a connecting bolt 11, and the tension and pressure sensor 9 is fixedly connected with the supporting seat end cover 101 through the connecting bolt 11. In the embodiment, the connecting bolt 11 passes through the bearing seat end cover 101 from the outside of the bearing seat 10 to the inside of the bearing seat 10 and is connected with the pull-pressure sensor 9, and the force value load loading of the control shaft 1 and the push-pull displacement sliding of the control shaft 1 can be controlled by adjusting the connecting bolt 11. In this embodiment, a cushion cover 12 is provided around the connecting bolt 11, and the cushion cover 12 is located between the tension/compression force sensor 9 and the support base end cover 101.
The tension and pressure sensor 9 is connected with the console through a signal wire, and electric signals generated by the tension and deformation of the tension and pressure sensor 9 are output and displayed by the console.
The outer peripheral wall of the hollow piston rod 6 is provided with a limit groove 62 for placing the limit part 7.
The diameter size of the through hole 61 in the 6 poles of hollow piston rod has been decided to the diameter size of control shaft 1, and the through hole 61 size can be bored according to 1 diameter sizes of different tail reduction gear control shafts in the 6 poles of hollow piston rod to satisfy the connection demand of the experimental different specifications control shaft of same set of power loading device. Once the diameter of the through hole in the hollow piston rod 6 is fixed, other control shafts 1 with the diameter smaller than that of the existing control shaft 1 need to be tested, only the connecting flange 3 and the connecting threaded sleeve 8 need to be replaced, and the control shaft 1 with the larger diameter needs to be tested, so that parts related to the load and the diameter in the device, such as two parts of the hollow piston rod 6 and the connecting threaded sleeve 8, are redesigned and manufactured according to the testing requirements of the diameter of the control shaft 1 and the force value load spectrum.
In this embodiment, the hollow piston rod 6 is provided with a web structure on the outer peripheral wall, the web structure is located in the servo cylinder 4 and divides the chamber in the servo cylinder 4 into a left chamber 411 and a right chamber 412, the left chamber 411 is arranged close to one side of the control shaft, the web structure defines the position of the hollow piston rod on the one hand, and on the other hand, the left chamber 411 and the right chamber 412 of the servo cylinder 4 are respectively sealed and isolated.
The working principle of the invention is as follows:
when a pulling force needs to be applied to the control shaft, hydraulic oil with a certain pressure is filled into a left cavity 411 of the servo oil cylinder 4 through a high-pressure oil pipe by an external servo oil source to push the hollow piston rod 6 and a supporting seat 10 in threaded connection with the hollow piston rod to move rightwards, the supporting seat 10 extrudes a connecting bolt 11 connected with a pulling pressure sensor 9, the pulling pressure sensor 9 is stretched and deformed to generate a voltage signal, and the voltage signal is transmitted to a force value instrument on the control console through a signal wire to be displayed; when pressure needs to be applied to the control shaft, hydraulic oil with certain pressure is filled into a right cavity 412 of the servo oil cylinder 4 through a high-pressure oil pipe by an external servo oil source to push the hollow piston rod 6 and the supporting seat 10 in threaded connection with the hollow piston rod to move left, the supporting seat 10 extrudes the cushion cover 12 connected with the pull-pressure sensor 9, the pull-pressure sensor 9 is compressed and deformed to generate a voltage signal, and the voltage signal is transmitted to a force value instrument on the control console through a signal wire to be displayed; an external hydraulic oil source is controlled by the servo valve 5 to fill the left chamber 411 or the right chamber 412 with oil.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to be limited thereto. Those skilled in the art can make numerous possible variations and modifications to the present invention, or modify equivalent embodiments to equivalent variations, without departing from the scope of the invention, using the teachings disclosed above. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention should fall within the protection scope of the technical scheme of the present invention, unless the technical spirit of the present invention departs from the content of the technical scheme of the present invention.
Claims (9)
1. The utility model provides a helicopter tail reduction gear operating shaft force loading test device which characterized in that: the device comprises a connecting flange (3), a servo oil cylinder (4), a hollow piston rod (6), a pulling pressure sensor (9) and a supporting seat (10), wherein one end of the connecting flange (3) is connected with a speed reducer casing (2), the other end of the connecting flange is connected with the servo oil cylinder (4), the hollow piston rod (6) sequentially penetrates through the connecting flange (3) and the servo oil cylinder (4) from the speed reducer casing (2) and is connected with the supporting seat (10), a rod inner through hole (61) is formed in the hollow piston rod (6) along the length direction, a speed reducer control shaft (1) extends from one end of the rod inner through hole (61) to the other end and reaches the inside of the supporting seat (10), the pulling pressure sensor (9) is located in the supporting seat (10) and is fixedly connected with the supporting seat (10), and the speed reducer control shaft (1) is connected with the pulling pressure sensor (9); the hollow piston rod (6) is provided with a radial plate structure on the peripheral wall, the radial plate structure is positioned in the servo oil cylinder (4) and divides the inner cavity of the servo oil cylinder (4) into a left cavity (411) and a right cavity (412), and the left cavity (411) is arranged close to one side of the control shaft.
2. The helicopter tail reducer control shaft force loading test device of claim 1, characterized in that: the helicopter tail speed reducer control shaft force loading test device further comprises a limiting piece (7), wherein the limiting piece (7) is located between the connecting flange (3) and the hollow piston rod (6) and used for preventing the hollow piston rod (6) from rotating.
3. The helicopter tail reducer control shaft force loading test device of claim 1, characterized in that: the helicopter tail speed reducer control shaft force loading test device further comprises a connecting threaded sleeve (8), and the connecting threaded sleeve (8) is used for connecting the speed reducer control shaft (1) with a pulling pressure sensor (9).
4. The helicopter tail reducer control shaft force loading test device of any one of claims 1 to 3, characterized in that: the servo oil cylinder (4) comprises an oil cylinder body (41), an oil cylinder front end cover (42) and an oil cylinder rear end cover (43), the hollow piston rod (6) penetrates through the oil cylinder front end cover (42) to enter the oil cylinder body (41) and penetrates out of the oil cylinder rear end cover (43), and the hollow piston rod (6) is connected with the oil cylinder front end cover (42) and the oil cylinder rear end cover (43) in a sealing mode.
5. The helicopter tail reducer control shaft force loading test device of claim 4, characterized in that: the connecting flange (3) is connected with the front end cover (42) of the oil cylinder.
6. The helicopter tail reducer control shaft force loading test device of any one of claims 1 to 3, characterized in that: and one end of the support seat (10) far away from the hollow piston rod (6) is provided with a support seat end cover (101), and the pull pressure sensor (9) is fixedly connected with the support seat end cover (101).
7. The helicopter tail reducer control shaft force loading test device of claim 6, characterized in that: the helicopter tail speed reducer control shaft force loading test device further comprises a connecting bolt (11), and the tension and pressure sensor (9) is fixedly connected with the support seat end cover (101) through the connecting bolt (11).
8. The helicopter tail reducer control shaft force loading test device of claim 6, characterized in that: and a limiting groove (62) for placing the limiting part (7) is formed in the peripheral wall of the hollow piston rod (6).
9. The helicopter tail reducer control shaft force loading test device of claim 7, characterized in that: a cushion cover (12) is sleeved outside the connecting bolt (11), and the cushion cover (12) is positioned between the tension and pressure sensor (9) and the supporting seat end cover (101).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010590504.9A CN111707469B (en) | 2020-06-24 | 2020-06-24 | Helicopter tail reducer control shaft force loading test device |
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| CN202010590504.9A CN111707469B (en) | 2020-06-24 | 2020-06-24 | Helicopter tail reducer control shaft force loading test device |
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| CN111707469A CN111707469A (en) | 2020-09-25 |
| CN111707469B true CN111707469B (en) | 2022-06-14 |
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| CN116026695A (en) * | 2021-04-01 | 2023-04-28 | 中国航发常州兰翔机械有限责任公司 | Application method of aeroengine casing pressure test tool |
| CN117268739B (en) * | 2023-11-22 | 2024-04-02 | 西安翼为航空科技有限公司 | Helicopter tail speed reducer casing fatigue test device |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102047091A (en) * | 2008-04-11 | 2011-05-04 | 安维斯Sd法国股份有限公司 | Method and device for monitoring the quality, particularly the stiffness and the phase, of a hydroelastic joint |
| CN109187016A (en) * | 2018-10-12 | 2019-01-11 | 江苏理工学院 | A kind of rolling bearing loading device and its control method with transient impact function |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3709141A1 (en) * | 1987-03-20 | 1988-09-29 | Fraunhofer Ges Forschung | MULTI-AXIAL DRIVE ELEMENT |
| DE3802500C1 (en) * | 1988-01-28 | 1989-06-22 | Roboflex Ag, Weinfelden, Ch | |
| CN101614615B (en) * | 2009-07-03 | 2010-09-29 | 中国航空动力机械研究所 | Simulative loader of tail reducer of helicopter |
| CN101718658B (en) * | 2009-11-17 | 2011-11-09 | 重庆大学 | Device for testing dynamic stiffness and constant pressure of high-speed electric spindle |
| CN102230863B (en) * | 2011-04-12 | 2013-07-17 | 河南科技大学 | Flexible loading system of friction and wear testing machine |
| CN105241658B (en) * | 2015-11-04 | 2017-11-07 | 武汉科技大学 | A kind of varying load operating mode hydraulic cylinder elastohydrodynamic lubrication experimental provision |
| CN108757644A (en) * | 2018-07-26 | 2018-11-06 | 上海衡拓液压控制技术有限公司 | Jet pipe electrohydraulic servo valve fatigue loading experimental rig |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102047091A (en) * | 2008-04-11 | 2011-05-04 | 安维斯Sd法国股份有限公司 | Method and device for monitoring the quality, particularly the stiffness and the phase, of a hydroelastic joint |
| CN109187016A (en) * | 2018-10-12 | 2019-01-11 | 江苏理工学院 | A kind of rolling bearing loading device and its control method with transient impact function |
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Inventor after: Zhou Zhibin Inventor after: Liu Guoliang Inventor after: Li Xinxiang Inventor after: Huang Ronghua Inventor before: Zhou Zhibin Inventor before: Li Xinxiang Inventor before: Huang Ronghua |