CN210346613U - Laser correction device for helicopter main reducing gear deflection and tail transmission shaft alignment - Google Patents
Laser correction device for helicopter main reducing gear deflection and tail transmission shaft alignment Download PDFInfo
- Publication number
- CN210346613U CN210346613U CN201921458360.0U CN201921458360U CN210346613U CN 210346613 U CN210346613 U CN 210346613U CN 201921458360 U CN201921458360 U CN 201921458360U CN 210346613 U CN210346613 U CN 210346613U
- Authority
- CN
- China
- Prior art keywords
- laser
- tail
- hollow cavity
- deflection
- main reducer
- 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.)
- Active
Links
Images
Landscapes
- Length Measuring Devices By Optical Means (AREA)
Abstract
The utility model discloses a helicopter main reducer deflects and tail transmission shaft aligns laser correcting unit, include: the laser mounting base is mounted on the output end of the tail shaft of the main speed reducer; the laser is fixedly arranged in the hollow cavity of the laser mounting base; the laser position adjusting components are arranged in a plurality of groups, are uniformly arranged along the circumferential direction of the hollow cavity and penetrate through the hollow cavity to fix the laser; the bearing frame target is installed on a bearing frame of the tail transmission shaft, a round scale value is carved on the front face of the bearing frame target, and the outer edge of the bearing frame target is completely attached to the bearing frame. The utility model has the advantages that: the coaxiality of the tail transmission shaft, the verticality of the bearing seat and the deflection angle of the main reducer can be measured more accurately, conveniently and quantitatively by utilizing the point light source and the high parallelism of the laser, the installation positions of the main reducer, the tail reducer and the tail transmission shaft are correspondingly adjusted, the installation precision is improved, and the safety and the reliability of the helicopter are improved.
Description
Technical Field
The utility model relates to a helicopter transmission system technical field particularly, relates to a helicopter main reducer deflects and tail transmission shaft aligns laser correcting unit.
Background
The transmission system of the helicopter is used for collecting the power (torsional moment) output by the engine and transmitting the power to the rotor, the tail rotor and the related accessories according to a certain proportion and direction, so that the rotor, the tail rotor and the related accessories obtain corresponding working rotating speed and power. Therefore, the installation of the main reducer, the tail reducer and the tail transmission shaft and the coaxiality relationship of the tail reducer transmission output end, the tail transmission shaft and the tail reducer input end are of great importance to the power system of the helicopter.
The helicopter provides lift by the rotation of the main rotor, but at the same time generates a reaction torque for the helicopter, which is transmitted to the body through the main reducer. The reaction moment acts on the flexible structure connected with the main speed reducer and the machine body, and can generate torsional deformation, namely the main speed reducer deflects a certain angle on the main reducing installation platform, when the rotor rotates, the flexible structure continuously bears the reaction force of the rotor, and the reaction force is larger than the force of the main reducing horizontal vibration, and the flexible structure can generate plastic deformation in theory, namely the main speed reducer generates unrecoverable deflection. After a certain flight time is accumulated, the plastic deformation basically reaches a fixed value, and when the helicopter works again, the flexible structure can continuously generate torsional elastic deformation on the basis of the original plastic deformation under the reaction moment of the rotor wing. If the plastic deformation of the flexible structure is large, after the elastic deformation is superposed, the deflection angle of the main speed reducer is larger, and at the moment, a large inclination angle is generated between the tail reduction transmission output end of the main speed reducer and the tail transmission shaft; in addition, the joint between the final drive and the engine also generates large strain and vibration due to the deflection of the final drive.
In order to eliminate the influence of the horizontal exciting force (longitudinal and transverse) of the rotor wing on the fuselage, the main speed reducer of many helicopters is not rigidly connected with the helicopter, but a flexible vibration isolation system is adopted at the joint of the main speed reducer and the fuselage. Such as Z9 and Z19 helicopters, the final drive is secured to the fuselage reinforcing bulkhead and final drive platform by four support bars and a bottom suspension assembly, as shown in fig. 1. The bottom suspension assembly includes flexible fatigue bars, laminate stops, diagonal cross members, etc., which dampen longitudinal and lateral vibrations of the final drive. The longitudinal vibration and the transverse vibration of the main speed reducer are periodic and reciprocating, the amplitude is small, and the suspension assembly cannot generate plastic deformation theoretically. But actually, the failure phenomenon that the spline joint at the front section of the Z9 helicopter tail transmission shaft is damaged is high, and the phenomenon that the No. 2 fixed hoop of the tail transmission shaft is broken frequently (because the No. 1 hoop of the Z9 helicopter is rigidly fixed, the fixation is firm, larger tail shaft vibration is transmitted backwards, and the flexible hoop is broken at the No. 2 fixed seat); furthermore, the Z9 helicopter main reducer has high failure of loosening of the universal joint pin bushing at the connection position of the main reducer and the engine, and the failure is also related to the large strain and vibration generated at the connection position of the main reducer and the engine. In addition, because the traditional tail shaft alignment equipment observes the coaxiality of the tail transmission shaft and the verticality of the bearing seat, the errors are too large, the precision is too low, only qualitative observation can be performed, quantitative measurement cannot be performed, the operation is complicated, the requirement condition is high, and the equipment damage rate is high.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem, the utility model aims to provide a can measure main reducer deflection angle to can be more accurate, more convenient, quantitative measurement tail transmission shaft's axiality, the straightness's that hangs down device of bearing frame.
The utility model provides a helicopter main reducer deflects and tail transmission shaft aligns laser correcting unit, the device includes: the laser installation base comprises a rear seat and a hollow cavity body perpendicular to the rear seat, the rear seat is installed on the output end of a tail shaft of the main speed reducer, and the hollow cavity body is located at the geometric center of the rear seat;
a laser fixedly mounted inside the hollow cavity;
the laser position adjusting components are arranged in a plurality of groups, and each group of laser position adjusting components are uniformly arranged along the circumferential direction of the hollow cavity and penetrate through the hollow cavity to fix the laser;
the bearing pedestal target is arranged on a bearing pedestal of the tail transmission shaft, a round scale value is carved on the front surface of the bearing pedestal target, and the outer edge of the bearing pedestal target is completely attached to the bearing pedestal.
As a further improvement of the utility model, the back seat is the triangle seat, the triangle seat passes through three bolt fastening on the final drive shaft output of final drive shaft and is on the final drive shaft output.
As a further improvement of the present invention, the hollow cavity is a hollow cylinder.
As a further improvement of the present invention, the laser position adjusting member is located at both ends of the hollow cavity.
As a further improvement of the present invention, each of the laser position adjusting members is three or four mechanical screws.
As a further improvement of the utility model, the front end of the hollow cavity is provided with a light transmission adjusting baffle plate, and a light transmission small hole is arranged on the light transmission adjusting baffle plate.
As a further improvement, the output end of the main reducer is provided with a positioning fixture block.
As a further improvement, the laser installation base is made of light metal or hard organic polymer plastic.
As a further improvement of the present invention, the bearing seat target is a semi-transparent material or a specular reflection material.
As a further improvement of the present invention, the laser device and be provided with the laser device stabilizing rubber ring between the cavity, the laser device stabilizing rubber ring is fixed on the outside rubber ring mounting groove of the laser device.
The utility model has the advantages that: through adopting the laser instrument of high accuracy, install the laser instrument on laser instrument installation base to be connected with main reducer tail axle output, utilize the pointolite and the high parallelism of laser can be more accurate, more convenient, quantitative measurement tail transmission shaft's axiality, the straightness and the main reducer deflection angle that hang down of bearing frame, and the mounted position of corresponding adjustment main reducer, tail transmission shaft, improve the installation accuracy, thereby promote helicopter's security and reliability.
Drawings
Fig. 1 is a schematic structural view of a helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to an embodiment of the present invention;
fig. 2 is a schematic view of a laser mounting base and a laser assembly of a helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to an embodiment of the present invention;
fig. 3 is a schematic structural view of a laser mounting base of a helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to an embodiment of the present invention;
fig. 4 is a schematic structural view of a bearing seat target of a helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to an embodiment of the present invention;
fig. 5 is a schematic diagram of the front scale of the bearing seat target of the helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to the embodiment of the present invention;
fig. 6 is a schematic view of a verticality measuring scale of a helicopter main reducer deflection and tail transmission shaft alignment laser correcting device according to an embodiment of the present invention;
fig. 7 is a schematic view illustrating the installation of a laser and a stabilizing rubber ring of a helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to an embodiment of the present invention;
fig. 8 is a schematic structural view of a stabilizing rubber ring of a helicopter main reducer deflection and tail transmission shaft alignment laser correction device according to an embodiment of the present invention.
In the figure, the position of the upper end of the main shaft,
1. a rear seat; 2. a hollow cavity; 3. a laser; 4. a laser position adjusting part; 5. a bearing block target; 6. positioning a fixture block; 7. and (5) stabilizing the rubber ring.
Detailed Description
The present invention will be described in further detail below with reference to specific embodiments and with reference to the attached drawings.
a laser 3 fixedly installed inside the hollow cavity 2;
the laser position adjusting components 4 are arranged in a plurality of groups, and each group of laser position adjusting components 4 are uniformly arranged along the circumferential direction of the hollow cavity 2 and penetrate through the hollow cavity 2 to fix the laser 3;
and the bearing pedestal target 5 is arranged on a bearing pedestal of the tail transmission shaft, the front surface of the bearing pedestal target 5 is carved with a circular scale value, and the outer edge of the bearing pedestal target 5 is completely attached to the bearing pedestal.
Furthermore, the rear seat 1 is a triangular seat, and the triangular seat is fixed on the output end of the tail shaft of the main speed reducer through three bolts on the output end of the tail shaft of the main speed reducer.
Furthermore, the hollow cavity 2 is a hollow cylinder and is matched with the cylindrical laser 3, so that the laser 3 is conveniently fixed.
Furthermore, laser position adjusting parts 4 are located at two ends of the hollow cavity 2, if only one group of laser position adjusting parts 4 is provided, the output axes of the main speed reducer and the tail transmission shaft can only be ensured to be parallel to the laser emission line generally, and the two ends of the hollow cavity are respectively provided with one group of laser position adjusting parts 4, so that the output axes of the main speed reducer and the tail transmission shaft can be coincided with the laser emission line.
Further, each set of laser position adjusting components 4 is three or four mechanical screws, so that the position of the laser 3 can be adjusted more stably and accurately.
Furthermore, the front end of the hollow cavity 2 is provided with a light transmission adjusting baffle plate, and a light transmission small hole is formed in the light transmission adjusting baffle plate. If the performance of the laser light source is not excellent enough and the diameter of the laser light beam is too large, the size of the laser light spot can be adjusted by utilizing the baffle.
Furthermore, a positioning fixture block 6 is arranged at the output end of the main speed reducer. In the measuring process, the measurement can be carried out for a plurality of times, and the average value is taken, so that the precision can be further improved.
Furthermore, the laser installation base is made of light metal or hard organic polymer plastic, so that the elasticity is low, and installation and correction are facilitated.
The further bearing mount target 5 is a semi-transparent material or a specular reflective material. For convenient observation, the bearing seat target 5 is designed into a semi-transparent structure, laser is projected on the scale, and data are directly read towards the laser direction, so that the accuracy, the measurement convenience and the safety can be ensured. The reflecting target for measuring the non-perpendicularity of the bearing seat is designed to be a mirror surface material, the mirror surface is required to have high flatness and is vertical to the bottom surface of the bearing seat, the deviation is not more than 5', laser is used for incidence and reflection on the plane of the bearing seat target, and a perpendicularity measuring scale (shown in figure 6) vertical to the laser is arranged at the position of a distance L in front of the bearing seat target; the perpendicularity measuring scale, the reflection target and the laser are used in a combined mode, and measurement of the non-perpendicular angle of the bearing seat is achieved.
Further, a laser stabilizing rubber ring is arranged between the laser 3 and the hollow cavity body 2, the laser stabilizing rubber ring is fixed on a stabilizing rubber ring mounting groove outside the laser 3, as shown in fig. 7, and the structure of the stabilizing rubber ring is shown in fig. 8. Have elastic stable rubber ring, on the one hand can be fine fix laser instrument 3 fine inside cavity 2, on the other hand also is favorable to laser instrument position adjustment part 4 to adjust laser instrument 3.
Further, laser instrument 3 is the wireless control laser instrument, and the wireless control module of wireless control laser instrument includes power, signal transmitter, signal receiver and controller, and the power supplies power for the wireless control laser instrument, and signal receiver is connected with the input of controller, and the output and the wireless control laser instrument of controller are connected, and power, signal receiver and controller are installed inside the back seat, through the work of signal transmitter control wireless control laser instrument.
For the consideration of measurement accuracy, observation convenience and safety, a laser with moderate intensity and excellent unidirectionality is selected, the diameter of an emergent beam is small, the diameter of a light spot between 1m and 6m is not changed, the divergence angle of the laser is required to be less than or equal to 0.2mrad, the power is required to be less than or equal to 10mW, and the working temperature is as follows: the laser density is uniformly distributed at the temperature of minus 20-50 ℃, the shape is regular, and the on-off, the laser intensity and the laser mode of the laser can be wirelessly controlled. The signal receiver of the wireless control laser receives the instruction, and the controller controls the on-off, the intensity and the laser mode of the laser.
When in specific use:
the output axis of the tail transmission shaft is coincident with the laser emission line in an adjusting way, which is the most critical step of measurement by using the device. The output axis of the tail shaft of the main speed reducer cannot be actually observed, so that the coincidence of the output axis of the tail transmission shaft and a laser emission line can be determined through the following operations: after the positions of laser position adjusting parts 4 positioned at the front end and the rear end of the hollow cavity 2 are properly adjusted, when the main rotor shaft is slowly rotated, light spots formed on a bearing seat target 5 by laser are basically at a fixed position and do not rotate any more; at the moment, the laser emission line is superposed with the output axis of the tail transmission shaft.
After the adjustment of the steps is completed, the average value of the data indicated by the centers of the light spots of the laser on the five bearing seat targets 5 is the deflection angle of the main speed reducer, and the average difference of the measured data of the five bearing seats is the non-coaxial deviation of the bearing seats of the tail transmission shaft. If the laser formed light spot is too large and the center is not well measured, a light-transmitting adjusting baffle can be additionally arranged to adjust the diameter of the light spot.
In practice, it may happen that the laser position adjustment unit 4 is adjusted anyway, and when the main rotor shaft is rotated, the light spot formed by the laser on the bearing block target 5 cannot be kept at a fixed position, but is rotated by a small radius; at this time, the measurement can be calculated by the following method by the geometrical principle: in the process of rotating the main rotor wing, the circular track of the light spot is observed, and the center of the light spot is recordedMinimum to target center DminThen recording the maximum value D from the center of the light spot to the center of the targetmax. The main yaw angle D measured at this bearing seat is then (D)max±Dmin) And/2 (target eyes are in the track to the minus sign). Recording the value D from the center of the light spot to the center of the target when observing the circular track of the light spotmin，DmaxIn the process, a positioning fixture block 6 can be fixed on the output end of the tail shaft of the main reducer to assist in determining DminAnd DmaxAnd the measurement precision is improved.
When measuring the out of plumb degree of bearing frame, the target design of the out of plumb degree of measuring the bearing frame is the specular reflection material, utilizes laser at the planar incidence and the reflection of target, places one at bearing frame target front distance L department and puts a dull and stereotyped perpendicular with the laser, and the center is the light trap, and out of plumb degree deviation theta is d/2L, and d is the distance of light spot distance center on the straightness measurement scale that hangs down. The requirement on the placement verticality of the light-transmitting plate is not high, and the light-transmitting plate can be vertically seen visually (the verticality deviation of the light-transmitting plate is 5 degrees, the influence on the result is less than 1 percent, and the non-verticality deviation theta is less than 1').
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A helicopter main reducing gear deflection and tail transmission shaft alignment laser correcting unit is characterized by comprising:
the laser mounting base comprises a rear seat (1) and a hollow cavity (2) perpendicular to the rear seat (1), the rear seat (1) is mounted on the output end of a tail shaft of a main speed reducer, and the hollow cavity (2) is located at the geometric center of the rear seat (1);
a laser (3) fixedly mounted inside the hollow cavity (2);
the laser position adjusting components (4) are arranged in a plurality of groups, and each group of laser position adjusting components (4) are uniformly arranged along the circumferential direction of the hollow cavity (2) and penetrate through the hollow cavity (2) to fix the laser (3);
the bearing seat target (5) is installed on a bearing seat of the tail transmission shaft, a round scale value is carved on the front face of the bearing seat target (5), and the outer edge of the bearing seat target (5) is completely attached to the bearing seat.
2. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that the rear seat (1) is a triangular seat fixed on the output end of the tail shaft of the main reducer by three bolts on the output end of the tail shaft of the main reducer.
3. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that the hollow cavity (2) is a hollow cylinder.
4. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that the laser position adjustment components (4) are located at both ends of the hollow cavity (2).
5. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that each set of the laser position adjustment components (4) is three or four machine screws.
6. The helicopter main reducer deflection and tail drive shaft alignment laser correction device as claimed in claim 1, characterized in that a light transmission adjusting baffle is arranged at the front end of the hollow cavity (2), and the light transmission adjusting baffle is provided with a light transmission small hole.
7. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that the output end of the main reducer is provided with a positioning fixture block (6).
8. The helicopter main reducer deflection and tail drive shaft alignment laser correction device of claim 1, wherein the laser mounting base is a lightweight metal material or a rigid organic polymer plastic material.
9. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that the bearing block target (5) is a semi-transparent material or a specular reflection material.
10. The helicopter main reducer deflection and tail drive shaft alignment laser correction device according to claim 1, characterized in that a laser stabilizing rubber ring is arranged between the laser (3) and the hollow cavity (2), and the laser stabilizing rubber ring is fixed on a rubber ring installation groove outside the laser (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921458360.0U CN210346613U (en) | 2019-09-04 | 2019-09-04 | Laser correction device for helicopter main reducing gear deflection and tail transmission shaft alignment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921458360.0U CN210346613U (en) | 2019-09-04 | 2019-09-04 | Laser correction device for helicopter main reducing gear deflection and tail transmission shaft alignment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210346613U true CN210346613U (en) | 2020-04-17 |
Family
ID=70177005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921458360.0U Active CN210346613U (en) | 2019-09-04 | 2019-09-04 | Laser correction device for helicopter main reducing gear deflection and tail transmission shaft alignment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210346613U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113390368A (en) * | 2021-07-08 | 2021-09-14 | 南京航空航天大学 | Monocular vision-based helicopter transmission system concentricity measuring method |
| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
| CN114603219A (en) * | 2022-03-31 | 2022-06-10 | 中车青岛四方机车车辆股份有限公司 | Laser correction perpendicularity tapping device and tapping method |
| CN114705139A (en) * | 2022-03-25 | 2022-07-05 | 昌河飞机工业（集团）有限责任公司 | Engine angular deviation and concentricity adjusting device |
| CN114942000A (en) * | 2022-07-13 | 2022-08-26 | 成都国营锦江机器厂 | Detection and calibration method for tail transmission shaft of helicopter |
-
2019
- 2019-09-04 CN CN201921458360.0U patent/CN210346613U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113390368A (en) * | 2021-07-08 | 2021-09-14 | 南京航空航天大学 | Monocular vision-based helicopter transmission system concentricity measuring method |
| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
| CN114705139A (en) * | 2022-03-25 | 2022-07-05 | 昌河飞机工业（集团）有限责任公司 | Engine angular deviation and concentricity adjusting device |
| CN114603219A (en) * | 2022-03-31 | 2022-06-10 | 中车青岛四方机车车辆股份有限公司 | Laser correction perpendicularity tapping device and tapping method |
| CN114942000A (en) * | 2022-07-13 | 2022-08-26 | 成都国营锦江机器厂 | Detection and calibration method for tail transmission shaft of helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210346613U (en) | Laser correction device for helicopter main reducing gear deflection and tail transmission shaft alignment | |
| US4053123A (en) | Method and apparatus to determine need for rotor blade pitch adjustment and/or blade substitution | |
| CN104121145B (en) | Wind power plant with measuring device | |
| US9341474B2 (en) | Surveying device having a rotation mirror for optically scanning an environment | |
| EP3094557B1 (en) | Tip clearance measurement | |
| US20070076193A1 (en) | Laser scanning apparatus with improved optical features | |
| EP2343498B1 (en) | Method for adjusting the light source of an electronic alignment device | |
| CN109093379A (en) | Low-pressure turbo unit body Intelligent assembly platform | |
| DK2855930T3 (en) | A method for the installation of sensors in the rotor blades and the installation device | |
| CN213090703U (en) | Laser centering measuring device | |
| CN105509618A (en) | Deflection angle measurer of flap aileron | |
| KR20220025719A (en) | drive shaft monitoring system | |
| CN114942000B (en) | Detection and calibration method for tail transmission shaft of helicopter | |
| US6915582B1 (en) | Alignment structure | |
| CN108593288B (en) | Loading device for gear model photoelastic test | |
| CN110695677A (en) | Device and method for correcting ship shafting stern tube | |
| CN211305462U (en) | Correcting device for ship shafting stern tube | |
| CN208888498U (en) | A kind of laser radar optical axis adjustment means | |
| US4422757A (en) | Apparatus and method for optical phasing of helicopter main rotor blades | |
| CN210603573U (en) | Flexible plate rotary motion vibration detection device | |
| KR20110092524A (en) | Static balancing measuring apparatus | |
| CN110907944A (en) | Anti-shaking and anti-shaking optical distance measuring instrument | |
| CN114001941B (en) | Ship propulsion shafting exciting force centering loading and detecting device | |
| GB2056109A (en) | Two-axis mounting structure for a telescope | |
| CN205718900U (en) | A kind of automatic counterweight apparatus for pole coordinate measuring apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |