CN106005446B - Unmanned helicopter power output device adopting flexible connection - Google Patents
Unmanned helicopter power output device adopting flexible connection Download PDFInfo
- Publication number
- CN106005446B CN106005446B CN201610466817.7A CN201610466817A CN106005446B CN 106005446 B CN106005446 B CN 106005446B CN 201610466817 A CN201610466817 A CN 201610466817A CN 106005446 B CN106005446 B CN 106005446B
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- 230000005540 biological transmission Effects 0.000 claims abstract description 21
- 238000009434 installation Methods 0.000 claims abstract description 13
- 230000017525 heat dissipation Effects 0.000 claims description 10
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 8
- 239000003638 chemical reducing agent Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
Abstract
The invention discloses a power output device of an unmanned helicopter adopting flexible connection, which comprises an engine main shaft, a first rubber column bolt, a main shaft output shaft, a clutch, a flywheel, a second rubber column bolt, a gearbox input shaft, a gearbox, an output shaft and a belt pulley. According to the invention, through improving the rigid bolt connection, the rubber column bolt is customized, and in addition, the structures of the output shaft and the input shaft of the gearbox are redesigned, so that the problem of difficulty in keeping concentricity during installation is solved, the installation is simple and convenient, vibration is prevented from being transmitted to the gearbox, the belt pulley is prevented from being overheated, and the reliability of the power transmission system of the unmanned helicopter is improved.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of power output mechanical devices, in particular to the technical field of power output devices of unmanned helicopters adopting flexible connection.
[ background of the invention ]
A transmission system of a small helicopter taking an aviation piston engine as a power device generally comprises the engine, a main reducer, a main rotor shaft, a tail transmission shaft, a tail reducer, a tail propeller shaft and the like. Wherein, the engine transmits power to the main speed reducer in a gear transmission or belt transmission mode. The power output device, also called a power takeoff, is a device that outputs power of an engine to an external device, and can safely and frequently carry cut-in power during the operation of the engine to reasonably and effectively transmit the power of the engine to a use position, and a power output shaft in a power output system plays a role of transmitting torque.
Power transmission is a complicated link that exists among various mechanical device always, and the unmanned aerial vehicle helicopter is also a complicated process with power transmission main rotor by the engine, to engine power output structure in the past, mainly relies on the output of engine flywheel end, and the front end can only accomplish the output of the power of minority. Due to the objective characteristics of the engine, there must be a clutch in the power transmission, but there are shaft coupling problems whether power is transmitted through the clutch or directly to the transmission. The concentricity of the shaft to the shaft connection is important because the main shaft of the engine runs at high speed during operation. At present, a method of fastening a central hole and keeping the central hole by taper is adopted for shaft connection of a small engine, the small engine only needs to be fixed on the central hole by one bolt due to small output torque, and the small engine is assembled by adjusting the tightness of the bolt and depending on a dial indicator during assembly so as to ensure the concentricity.
But along with the maximization of present unmanned aerial vehicle helicopter, the application of double-cylinder, four jar engines, such fixed approach has not been practical yet, unmanned helicopter engine's rotational speed is high, if engine power take off's connection goes wrong, the axiality is not guaranteed, it is big to appear vibrating easily, power take off process deviation appears, simultaneously, bolt fastening makes the vibrations of engine during operation conduct on the gearbox input shaft, by gear at all levels in shock conduction gearbox again, and arouse resonance, this makes power take off unstable and all spare parts in the gearbox can appear metal fatigue in very short time, lead to the flight accident.
The power output requirement of the engine is higher and higher, the maximum static friction force generated between the belt pulley and the crankshaft cannot meet the requirement of high-power output due to the pretightening of the starting bolt of the front-end structure, and the front-end belt pulley of the front-end structure has a high-temperature phenomenon along with the prolonging of the working time, so that a belt for transmitting power is overheated, a certain belt burning phenomenon occurs, and the service life of the belt is influenced.
[ summary of the invention ]
The invention aims to solve the problems in the prior art, and provides a power output device of an unmanned helicopter, which adopts flexible connection, can be mounted simply and conveniently, ensures higher coaxiality, avoids vibration from being transmitted to a gearbox, prevents a belt pulley from being overheated, and improves the reliability of a power transmission system of the unmanned helicopter.
In order to achieve the purpose, the invention provides a power output device of an unmanned helicopter adopting flexible connection, which comprises an engine main shaft, a first rubber column bolt, a main shaft output shaft, a clutch, a flywheel, a second rubber column bolt, a gearbox input shaft, a gearbox, an output shaft and a belt pulley, wherein the engine main shaft is connected with one end of the main shaft output shaft through the first rubber column bolt, the other end of the main shaft output shaft is connected with one end of the clutch shaft through a meshing sleeve, the clutch shaft is sequentially sleeved with the clutch and the flywheel, and the other end of the clutch shaft is connected with the gearbox input shaft through the second rubber column bolt; one end of the engine main shaft is provided with a large threaded hole, one end of the main shaft output shaft is provided with a first bolt hole, one end of the clutch shaft is provided with a small threaded hole, and one end of the gearbox input shaft is provided with a second bolt hole.
Preferably, the number of the large threaded holes is two, and the large threaded holes are matched with the first rubber stud bolts for installation; the quantity of first bolt hole is a, and first bolt hole is installed with the rubber column cooperation of first rubber column bolt.
Preferably, the number of the small threaded holes is two, and the small threaded holes are matched with the second rubber column bolts; the quantity of second bolt hole is a, and the second bolt hole is installed with the rubber column cooperation of second rubber column bolt.
Preferably, the clutch shaft is sleeved with a clutch housing, the clutch and the flywheel are both arranged in the clutch housing, and the clutch is connected with the second bearing.
Preferably, a first bearing is mounted outside the output shaft, the first bearing supports a spindle output shaft housing, and the spindle output shaft housing and the clutch housing are mounted in a bolted connection.
Preferably, the center of the main shaft of the engine is provided with a hole I, the center of the output shaft of the main shaft is provided with a hole II, and a first rubber column is arranged in the hole I and the hole II; a hole III is formed in the center of the clutch shaft, a hole IV is formed in the center of the input shaft of the gearbox, and a second rubber column is arranged in the hole III and the hole IV.
Preferably, the main shaft output shaft is provided with a spline, the meshing sleeve is of an internal gear structure, and the meshing sleeve is sleeved on the spline and can axially slide on the main shaft output shaft.
Preferably, the clutch shaft is fitted with a gear, external teeth of the gear mesh with internal teeth of the meshing sleeve, and the main shaft output shaft rotates together with the clutch shaft to transmit power and to cut off power when disengaged.
Preferably, the output shaft and the input shaft of the gearbox are integrally connected, a shaft sleeve is sleeved on the output shaft, and the shaft sleeve and the gearbox are connected and installed through bolts.
Preferably, a belt pulley is mounted at one end of the output shaft, heat dissipation holes are formed in the end face of the belt pulley, and the heat dissipation holes are distributed along the circumference of the end face of the belt pulley; the belt pulley can be driven by any one of V belt, synchronous belt, flat belt and the like.
The invention has the beneficial effects that: the connection mode of the invention is completely different from the connection mode of the original power output device, the original power output device is rigidly connected by bolts, the installation and debugging are troublesome, and the vibration is easily transmitted into the gearbox, so that the power output is unstable and is easily damaged to cause accidents. The invention improves the rigid bolt connection, customizes the rubber column bolt, redesigns the structures of the main shaft output shaft and the gearbox input shaft, and opens the hole for connecting the rubber column. The rubber column bolt is elastically connected with the main shaft of the engine and the output shaft of the main shaft, the clutch shaft and the input shaft of the gearbox, so that the problem of difficulty in keeping coaxiality during installation is solved, the coaxiality of the main shaft, the clutch and the spline shaft of the engine is ensured, the smoothness of power output of the engine is ensured, the probability of damaging the clutch and the main shaft in the power output process is reduced, the bearing of the output shaft is lubricated in an oil bath, larger power can be transmitted, the phenomenon that a belt is burnt out due to overhigh temperature of the belt pulley can be prevented through heat dissipation holes in the belt pulley, and the service life; the installation is simple and convenient, can reduce the vibration, guarantees the steady of engine power take off, avoids vibrations to conduct the gearbox for unmanned helicopter power transmission system reliability improves.
The features and advantages of the present invention will be described in detail by embodiments in conjunction with the accompanying drawings.
[ description of the drawings ]
FIG. 1 is a front sectional view of a power take-off device of an unmanned helicopter using flexible connection according to the present invention;
FIG. 2 is a schematic view of a rubber stud of the power take-off of an unmanned helicopter of the present invention using a flexible connection;
FIG. 3 is a schematic illustration of a transmission input shaft of an unmanned helicopter power take-off employing a flexible coupling of the present invention;
fig. 4 is a schematic view of a pulley heat dissipation hole of an unmanned helicopter power take-off device adopting flexible connection according to the present invention.
In the figure: 1-an engine main shaft, 2-a first rubber column bolt, 3-a first rubber column, 4-a main shaft output shaft shell, 5-a first bearing, 6-an output shaft, 61-a first bolt hole, 62-a hole II, 7-a spline, 8-a meshing sleeve, 9-a clutch shell, 10-a clutch shaft, 101-a small thread hole, 102-a hole III and 11-a second rubber column bolt, 12-a gearbox, 13-a gearbox input shaft, 131-a hole IV, 132-a second bolt hole, 14-a second rubber column, 15-a flywheel, 16-a clutch, 17-a second bearing, 18-a gear, 19-a hole I, 20-a big threaded hole, 21-a shaft sleeve, 22-an output shaft, 23-a belt pulley and 231-a heat dissipation hole.
[ detailed description ] embodiments
Referring to fig. 1 to 4, the engine main shaft comprises an engine main shaft 1, a first rubber stud 2, a main shaft output shaft 6, a clutch shaft 10, a clutch 16, a flywheel 15, a second rubber stud 11, a gearbox input shaft 13, a gearbox 12, an output shaft 22 and a belt pulley 23, wherein the engine main shaft 1 is connected with one end of the main shaft output shaft 6 through the first rubber stud 2, the other end of the main shaft output shaft 6 is connected with one end of the clutch shaft 10 through a meshing sleeve 8, the clutch shaft 10 is sequentially sleeved with the clutch 16 and the flywheel 15, and the other end of the clutch shaft 10 is connected with the gearbox input shaft 13 through the second rubber stud 11; one end of the engine main shaft 1 is provided with a large threaded hole 20, one end of the main shaft output shaft 6 is provided with a first bolt hole 61, one end of the clutch shaft 10 is provided with a small threaded hole 101, and one end of the gearbox input shaft 13 is provided with a second bolt hole 132.
The number of the large threaded holes 20 is 6, and the large threaded holes 20 are matched with the first rubber stud bolts 2; the number of the first bolt holes 61 is 6, and the first bolt holes 61 are installed in cooperation with the rubber columns of the first rubber column bolts 2. The number of the small threaded holes 101 is 6, and the small threaded holes 101 are matched with the second rubber stud bolts 11; the number of the second bolt holes 132 is 6, and the second bolt holes 132 are installed in cooperation with the rubber posts of the second rubber post bolt 11. The clutch shaft 10 is sleeved with a clutch shell 9, a clutch 16 and a flywheel 15 are both arranged in the clutch shell 9, and the clutch 16 is connected with a second bearing 17. A first bearing 5 is installed outside the main shaft output shaft 6, a main shaft output shaft shell 4 is supported by the first bearing 5, and the main shaft output shaft shell 4 and the clutch shell 9 are installed in a bolt connection mode. A hole I19 is formed in the center of the main shaft 1 of the engine, a hole II 62 is formed in the center of the main shaft output shaft 6, and a first rubber column 3 is installed in the hole I19 and the hole II 62; a hole III 102 is formed in the center of the clutch shaft 10, a hole IV 131 is formed in the center of the transmission input shaft 13, and a second rubber column 14 is installed in the hole III 102 and the hole IV 131. The main shaft output shaft 6 is provided with a spline 7, the meshing sleeve 8 is of an internal gear structure, and the meshing sleeve 8 is sleeved on the spline 7 and can axially slide on the main shaft output shaft 6. The clutch shaft 10 is sleeved with a gear 18, the outer teeth of the gear 18 are meshed with the inner teeth of the meshing sleeve 8, the main shaft output shaft 6 and the clutch shaft 10 rotate together to realize power transmission, and power cut-off is realized when the power is disengaged. The output shaft 22 and the gearbox input shaft 13 are connected into a whole, a shaft sleeve 21 is sleeved on the output shaft 22, and the shaft sleeve 21 and the gearbox 12 are connected and installed through bolts. The belt pulley 23 is installed at one end of the output shaft 22, a heat dissipation hole 231 is formed in the end face of the belt pulley 23, and the heat dissipation holes 231 are distributed along the circumference of the end face of the belt pulley 23. The power output end adopts a belt transmission mode, the arrangement is flexible, and the belt pulley 23 can adopt any one of V belt, synchronous belt, flat belt and the like for transmission.
The working process of the invention is as follows:
in the working process of the power output device of the unmanned helicopter adopting the flexible connection, after an engine is started, a crankshaft drives a flywheel 15 and a clutch 16 to rotate, power is transmitted to a gearbox from the clutch 16, an output shaft of the gearbox directly drives a belt pulley 23, and the belt pulley 23 transmits the power to a main rotor shaft of the helicopter after being decelerated in a belt transmission mode.
The specific process comprises the following steps: the main shaft 1 of the engine is connected with a main shaft output shaft 6 through 6 first rubber column bolts 2 and first rubber columns 3, the main shaft output shaft 6 is connected with a clutch 10 shaft through a meshing sleeve 8, the meshing sleeve 8 is of an internal gear structure, and the meshing sleeve 8 is sleeved on a spline 63 and can axially slide on the main shaft output shaft 6. The inner teeth of the meshing sleeve 8 are meshed with the outer teeth of the gear 18, the main shaft output shaft 6 and the clutch shaft 10 rotate together to realize power transmission, and power cut-off is realized when the power is disengaged; the clutch shaft 10 is connected to a transmission input shaft 13 via 6 second rubber studs 11 and a second rubber stud 14, so that power is output from the engine.
The connection mode of the invention is completely different from the connection mode of the original power output device, the original power output device is rigidly connected by bolts, the installation and debugging are troublesome, and the vibration is easily transmitted into the gearbox, so that the power output is unstable and is easily damaged to cause accidents. The invention improves the rigid bolt connection, customizes the rubber column bolt 11, redesigns the structures of the main shaft output shaft 6 and the gearbox input shaft 13, and opens the hole for connecting the rubber column. The rubber column bolt 11 is elastically connected with the main shaft 1 of the engine and the main shaft output shaft 6, the clutch shaft 10 and the gearbox input shaft 13, the problem that the coaxiality is difficult to keep during installation is solved, the coaxiality of the main shaft, the clutch and the spline shaft of the engine is ensured, the smoothness of power output of the engine is ensured, the probability of damaging the clutch and the main shaft in the power output process is reduced, the output shaft bearing is lubricated in oil bath, larger power can be transmitted, the phenomenon that a belt is burnt out due to overhigh temperature of the belt pulley 23 can be prevented through heat dissipation holes in the belt pulley 23, and the service life of the belt is prolonged; the installation is simple and convenient, can reduce the vibration, guarantees the steady of engine power take off, avoids vibrations to conduct the gearbox for unmanned helicopter power transmission system reliability improves.
The above embodiments are illustrative of the present invention, and are not intended to limit the present invention, and any simple modifications of the present invention are within the scope of the present invention.
Claims (6)
1. The utility model provides an adopt flexible coupling's unmanned helicopter power take-off which characterized in that: the engine main shaft (1) is connected with one end of the main shaft output shaft (6) through the first rubber column bolt (2), the other end of the main shaft output shaft (6) is connected with one end of the clutch shaft (10) through a meshing sleeve (8), the clutch (16) and the flywheel (15) are sequentially sleeved on the clutch shaft (10), and the other end of the clutch shaft (10) is connected with the gearbox input shaft (13) through the second rubber column bolt (11); one end of the engine main shaft (1) is provided with a large threaded hole (20), one end of the main shaft output shaft (6) is provided with a first bolt hole (61), one end of the clutch shaft (10) is provided with a small threaded hole (101), and one end of the gearbox input shaft (13) is provided with a second bolt hole (132); the number of the large threaded holes (20) is 6, and the large threaded holes (20) are matched with the first rubber column bolts (2) for installation; the number of the first bolt holes (61) is 6, and the first bolt holes (61) are matched with rubber columns of the first rubber column bolts (2) for installation; the number of the small threaded holes (101) is 6, and the small threaded holes (101) are matched with the second rubber stud bolts (11) for installation; the number of the second bolt holes (132) is 6, and the second bolt holes (132) are matched with rubber columns of the second rubber column bolts (11) for installation; a hole I (19) is formed in the center of the engine spindle (1), a hole II (62) is formed in the center of the spindle output shaft (6), and a first rubber column (3) is installed in the hole I (19) and the hole II (62); a hole III (102) is formed in the center of the clutch shaft (10), a hole IV (131) is formed in the center of the transmission input shaft (13), and a second rubber column (14) is installed in the hole III (102) and the hole IV (131); a belt pulley (23) is mounted at one end of the output shaft (22), heat dissipation holes (231) are formed in the end face of the belt pulley (23), and the heat dissipation holes (231) are distributed along the circumference of the end face of the belt pulley (23); the belt pulley (23) can be driven by any one of V belt, synchronous belt, flat belt and the like.
2. The power output device of the unmanned helicopter with flexible connection as claimed in claim 1, characterized in that: the clutch shaft (10) is sleeved with a clutch shell (9), the clutch (16) and the flywheel (15) are both installed in the clutch shell (9), and the clutch (16) is connected with the second bearing (17).
3. The power output device of the unmanned helicopter with flexible connection as claimed in claim 2, characterized in that: a first bearing (5) is installed outside the main shaft output shaft (6), a main shaft output shaft shell (4) is supported by the first bearing (5), and the main shaft output shaft shell (4) and the clutch shell (9) are installed in a bolt connection mode.
4. The power output device of the unmanned helicopter with flexible connection as claimed in claim 1, characterized in that: the main shaft output shaft (6) is provided with a spline (7), the meshing sleeve (8) is of an internal gear structure, and the meshing sleeve (8) is sleeved on the spline (7) and can axially slide on the main shaft output shaft (6).
5. The power output device of the unmanned helicopter with flexible connection as claimed in claim 1, characterized in that: the clutch shaft (10) is sleeved with a gear (18), external teeth of the gear (18) are meshed with internal teeth of the meshing sleeve (8), the spindle output shaft (6) and the clutch shaft (10) rotate together to transmit power, and power is cut off when the spindle output shaft and the clutch shaft are disengaged.
6. The power output device of the unmanned helicopter with flexible connection as claimed in claim 1, characterized in that: the output shaft (22) and the input shaft (13) of the gearbox are integrally connected, a shaft sleeve (21) is sleeved on the output shaft (22), and the shaft sleeve (21) and the gearbox (12) are connected and installed through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610466817.7A CN106005446B (en) | 2016-06-22 | 2016-06-22 | Unmanned helicopter power output device adopting flexible connection |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610466817.7A CN106005446B (en) | 2016-06-22 | 2016-06-22 | Unmanned helicopter power output device adopting flexible connection |
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| Publication Number | Publication Date |
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| CN106005446A CN106005446A (en) | 2016-10-12 |
| CN106005446B true CN106005446B (en) | 2021-02-05 |
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| CN201610466817.7A Active CN106005446B (en) | 2016-06-22 | 2016-06-22 | Unmanned helicopter power output device adopting flexible connection |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516101B (en) * | 2016-11-30 | 2018-11-23 | 中国直升机设计研究所 | A kind of lifting airscrew tower rotor connector |
| CN110594313A (en) * | 2019-09-23 | 2019-12-20 | 浙江铃丰科技有限公司 | Novel clutch assembly |
| CN111457075B (en) * | 2020-03-31 | 2021-07-27 | 中国航发湖南动力机械研究所 | Antifriction device and aircraft transmission system main reducer |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201240501Y (en) * | 2008-06-06 | 2009-05-20 | 中国航空动力机械研究所 | Speed reducing driver for helicopter rotor |
| CN101610949A (en) * | 2007-01-15 | 2009-12-23 | Gif工业研究有限责任公司 | Aircraft propeller drive is used to drive method, the purposes of aircraft propeller drive bearing and the purposes of motor of properller |
| CN202118185U (en) * | 2011-07-02 | 2012-01-18 | 济南吉美乐电源技术有限公司 | Damping and supporting device of thermal-insulating shield |
| EP2815981A1 (en) * | 2013-06-21 | 2014-12-24 | Hamilton Sundstrand Corporation | Propeller rotor and engine overspeed control |
| CN105041962A (en) * | 2014-04-25 | 2015-11-11 | 通用汽车环球科技运作有限责任公司 | Torsional vibration damper for drive train |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2964948B1 (en) * | 2010-09-16 | 2012-08-31 | Eurocopter France | ROTARY VESSEL AIRCRAFT WITH A PROPULSIVE MEANS AND METHOD APPLIED THERETO |
-
2016
- 2016-06-22 CN CN201610466817.7A patent/CN106005446B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101610949A (en) * | 2007-01-15 | 2009-12-23 | Gif工业研究有限责任公司 | Aircraft propeller drive is used to drive method, the purposes of aircraft propeller drive bearing and the purposes of motor of properller |
| CN201240501Y (en) * | 2008-06-06 | 2009-05-20 | 中国航空动力机械研究所 | Speed reducing driver for helicopter rotor |
| CN202118185U (en) * | 2011-07-02 | 2012-01-18 | 济南吉美乐电源技术有限公司 | Damping and supporting device of thermal-insulating shield |
| EP2815981A1 (en) * | 2013-06-21 | 2014-12-24 | Hamilton Sundstrand Corporation | Propeller rotor and engine overspeed control |
| CN105041962A (en) * | 2014-04-25 | 2015-11-11 | 通用汽车环球科技运作有限责任公司 | Torsional vibration damper for drive train |
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| CN106005446A (en) | 2016-10-12 |
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Effective date of registration: 20210115 Address after: 312500-1, building 3, No. 39, Yulin Road, Xinchang County, Shaoxing City, Zhejiang Province Applicant after: Xinchang Chengsheng Machinery Technology Co.,Ltd. Address before: 312500, No. 38, changwan village, Nanniwan street, Nanming street, Xinchang County, Shaoxing City, Zhejiang Province Applicant before: XINCHANG QIXING STREET RUIXIN MACHINERY PLANT |
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Effective date of registration: 20231027 Address after: No. 19 Xinhuan Road, Nanming Street, Xinchang County, Shaoxing City, Zhejiang Province, 312500 Patentee after: Xinchang County Lina Silk Knitting Factory Address before: 312500-1, building 3, No. 39, Yulin Road, Xinchang County, Shaoxing City, Zhejiang Province Patentee before: Xinchang Chengsheng Machinery Technology Co.,Ltd. |
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Denomination of invention: A Power Output Device for Unmanned Helicopters Using Soft Connection Effective date of registration: 20231031 Granted publication date: 20210205 Pledgee: Bank of China Limited by Share Ltd. Xinchang branch Pledgor: Xinchang County Lina Silk Knitting Factory Registration number: Y2023330002505 |
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