CN111268113B - Bevel gear configuration coaxial double-rotor speed change transmission mechanism - Google Patents
Bevel gear configuration coaxial double-rotor speed change transmission mechanism Download PDFInfo
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- CN111268113B CN111268113B CN202010125482.9A CN202010125482A CN111268113B CN 111268113 B CN111268113 B CN 111268113B CN 202010125482 A CN202010125482 A CN 202010125482A CN 111268113 B CN111268113 B CN 111268113B
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- bevel gear
- output shaft
- gear
- coaxial
- speed
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 44
- 230000008859 change Effects 0.000 title claims abstract description 17
- 230000007246 mechanism Effects 0.000 title claims abstract description 14
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 17
- 230000009977 dual effect Effects 0.000 claims description 13
- 208000032369 Primary transmission Diseases 0.000 claims description 3
- 208000032370 Secondary transmission Diseases 0.000 claims description 3
- 230000009467 reduction Effects 0.000 abstract description 8
- 238000000034 method Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
- F16H1/2854—Toothed gearings for conveying rotary motion with gears having orbital motion involving conical gears
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Retarders (AREA)
- Gear Transmission (AREA)
- Structure Of Transmissions (AREA)
Abstract
The invention discloses a bevel gear configuration coaxial double-rotor speed change transmission mechanism. Which comprises a staged reduction device and a coaxial reduction device. The grading speed reducer mainly completes the power multipath flow division through the three-stage gear transmission mechanism, simultaneously realizes the torque distribution and the speed reduction function, and reduces the load and the linear speed born by the gears. The coaxial speed reducer comprises an upper bevel gear and a lower bevel gear which are coaxial back to back, the upper bevel gear is fixedly connected with the lower rotor through an output shaft, and the lower bevel gear is fixedly connected with the upper rotor through a planetary speed reducing mechanism, so that the power output of the double rotors with opposite rotating directions is realized. The invention discloses a transmission mechanism which has the advantages of strong bearing capacity, high efficiency and the like, and can be applied to the fields of high-speed helicopters, ship transmission systems and the like.
Description
Technical Field
The invention relates to a power transmission system of a helicopter, in particular to a bevel gear configuration coaxial double-rotor speed change transmission mechanism.
Background
The flying speed of the high-speed helicopter can reach more than 400km/h, and the main configuration of the high-speed helicopter is a coaxial main rotor wing with tail rotor configuration. In order to avoid forward blade shock waves when the helicopter flies forward at high speed, the rotating speed of the rotor wing needs to be reduced. The reduction of the rotor speed can be achieved by engine speed change and transmission system speed change, the normal working speed range of the engine is small, and the amplitude of the rotor speed reduction by reducing the engine speed is limited, so that the transmission system speed change is necessary.
Currently, transmission speed changing devices for aviation can be divided into two categories: the clutch speed variator mainly utilizes the differential overrunning performance of overrunning clutch to realize the output of two different speeds. The other type is a differential planetary transmission, and the output of different rotational speeds is realized mainly by controlling the speed of a gear ring. The transmission scheme of the variable transmission ratio can be realized in principle, but has some technical difficulties. If a clutch speed changing device scheme is adopted, the technical difficulties of friction, impact, power loss and the like of a clutch in the transition process of multi-disc clutch control are overcome; while using a differential planetary transmission scheme requires another variable speed drive unit, engine control and flight control of the shifting process also require exploration verification. In addition, variable ratio drive trains result in an increased number of parts, increased mass, and reduced reliability and efficiency of the drive train.
Therefore, when the high-speed helicopter is developed, a key attack is carried out on the transmission system, the lifting potential of the forward blade is fully exerted, the limit of the forward flying speed of the conventional helicopter is broken through, and the method is a key technology of the high-speed helicopter.
Disclosure of Invention
In view of the above, the invention provides a bevel gear configuration coaxial double-rotor speed change transmission mechanism for solving the problems of small bearing capacity, low flying speed and the like of a high-speed helicopter in the prior art.
In order to solve the problems existing in the prior art, the technical scheme of the invention is as follows: a bevel gear configuration coaxial double-rotor speed change transmission mechanism is characterized in that: comprises a grading speed reducer and a coaxial speed reducer; the grading speed reducer is a three-stage fixed-axis gear train consisting of I-stage gear transmission, II-stage gear transmission and III-stage gear transmission;
the I-stage gear transmission comprises a primary driving wheel and two driven face gears, and the primary driving wheel is meshed with the two driven face gears at the same time to realize primary transmission;
the II-stage gear transmission comprises two secondary driving wheels and four secondary driven wheels, wherein each secondary driving wheel is coaxial with one driven face gear and is meshed with the two secondary driven wheels at the same time, so that secondary transmission is realized;
the III-level gear transmission comprises four three-level driving wheels and eight three-level driven wheels, wherein each three-level driving wheel is coaxial with one two-level driven wheel and is meshed with two three-level driven wheels at the same time, so that three-level transmission is realized;
the coaxial speed reducer comprises an upper bevel gear, a lower bevel gear and a planetary speed change mechanism which are back to back; the upper bevel gear is meshed with the four three-stage driven wheels and fixedly connected with the first output shaft; the lower bevel gear is meshed with the other four three-stage driven wheels and is fixedly connected with the sun gear through the second output shaft to drive the planet carrier, and the planet carrier is fixedly connected with the third output shaft to finish speed change and contra-rotation double output.
Further, the upper bevel gear is also meshed with the upper tail gear, and the lower bevel gear is also meshed with the lower tail gear.
Further, a thrust bearing is arranged between the upper bevel gear and the lower bevel gear.
Further, the first output shaft, the second output shaft and the third output shaft are hollow shafts, and the two ends of the third output shaft are provided with splines; the aperture of the first output shaft and the aperture of the second output shaft are both larger than the shaft diameter of the third output shaft, and the third output shaft passes through the centers of the first output shaft and the second output shaft and is higher than the first output shaft.
Further, the rotational speeds of the first output shaft and the third output shaft are different and the directions of the rotation are opposite.
Further, the number of the grading speed reducing devices is at least 1, and when multiple paths of input are adopted, each path has the same configuration and is uniformly distributed along the circumference.
Compared with the prior art, the invention has the following advantages:
1) The hierarchical speed reducer is a three-stage fixed-axis gear train, adopts an integrated design of a shaft, a bearing and a gear, effectively reduces the transmission load of the gear and the quality of the system, and ensures that the system has compact structure and high reliability.
2) The invention realizes the functions of decelerating and reversing power simultaneously through the back-to-back coaxial bevel gears supported by the thrust bearing, and has simple structure, convenient installation and good stability compared with the traditional reversing mechanism.
3) The whole transmission system has obvious space arrangement level, the grading speed reducer and the upper bevel gear and the lower bevel gear are arranged on the upper layer in a blocky manner along the circumference, and the planetary speed change device is arranged on the lower layer, so that the modularized design of the speed reducer is facilitated, and the system is convenient to install, disassemble and maintain.
4) In the speed-changing transmission method for realizing the double rotor wings, the planetary speed-changing device scheme is adopted, the transmission is stable, the friction and impact of a system can be obviously reduced, meanwhile, the speed-changing transmission method also has a larger transmission ratio, the requirement of adopting lower rotation speed output when the high-speed helicopter flies at a high speed is easily met, and the technical problems of friction, impact, power loss and the like in the traditional clutch speed-changing device scheme are solved.
5) The last stage of the invention uses the back-to-back coaxial bevel gears with larger size, so the diameter of the output shaft can be designed to be larger, and related devices such as an internal operating device, an ice preventing and removing device, a testing device and the like can be more easily arranged in the output shaft.
Description of the drawings:
FIG. 1 is a schematic illustration of a single engine input bevel gear configuration coaxial dual rotor variable speed drive of the present invention;
FIG. 2 is an isometric side view of a dual engine input bevel gear configuration coaxial dual rotor variable speed drive of the present invention;
FIG. 3 is a top view of a dual engine input bevel gear configuration coaxial dual rotor variable speed drive of the present invention;
FIG. 4 is a schematic illustration of the dual engine input bevel gear configuration coaxial dual rotor variable speed drive of the present invention in combination with dual rotors;
reference numerals: 1. a power input shaft, 2, a primary driving wheel, 3, a first driven face gear, 4, a second driven face gear, 5, a first secondary driving wheel, 6, a second driving wheel, 7, a first secondary driven wheel, 8, a second driven wheel, 9, a third secondary driven wheel, 10, a fourth secondary driven wheel, 11, a first tertiary driving wheel, 12, a second tertiary driving wheel, 13, a third tertiary driving wheel, 14, a fourth tertiary driving wheel, 15, a first tertiary driven bevel gear, 16, a second tertiary driven bevel gear, 17, a third tertiary driven bevel gear, 18, a fourth-stage driven bevel gear, 19, a fifth-stage driven bevel gear, 20, a sixth-stage driven bevel gear, 21, a seventh-stage driven bevel gear, 22, an eighth-stage driven bevel gear, 23, an upper bevel gear, 24, a lower bevel gear, 25, a thrust bearing, 26, a first output shaft, 27, a second output shaft, 28, a third output shaft, 29, an upper tail wing gear, 30, a lower tail wing gear, 31, a sun gear, 32, a planet wheel, 33, an annular gear, 34, a planet carrier, 35, an upper rotor wing, 36 and a lower rotor wing.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Embodiment one:
the present embodiment provides a bevel gear configuration coaxial dual rotor variable speed drive for single engine input, as shown in fig. 1: comprises a grading speed reducer and a coaxial speed reducer; the grading speed reduction device comprises a power input shaft 1, wherein the power input shaft 1 is fixedly connected with a primary driving wheel 2 to realize primary transmission; the primary driving wheel 2 is meshed with the first driven face gear 3 and the second driven face gear 4 at the same time, and adopts radial floating support to finish primary distribution of power; the first driven face gear 3 and the second driven face gear 4 are respectively fixedly connected with a first secondary driving wheel 5 and a second driving wheel 6 through a torsion shaft, so that secondary transmission is realized; the first secondary driving wheel 5 is simultaneously meshed with the first secondary driven wheel 7 and the second driven wheel 8; the second-stage driving wheel 6 is simultaneously meshed with the third-stage driven wheel 9 and the fourth-stage driven wheel 10, so that the secondary distribution of the power is completed; the first secondary driven wheel 7, the second secondary driven wheel 8, the third secondary driven wheel 9 and the fourth secondary driven wheel 10 are respectively fixedly connected with a first tertiary driving wheel 11, a second tertiary driving wheel 12, a third tertiary driving wheel 13 and a fourth tertiary driving wheel 14 through double shafts so as to realize three-level transmission; the first-stage driving wheel 11 is meshed with the first-stage driven bevel gear 15 and the second-stage driven bevel gear 16 simultaneously; the second-stage driving wheel 12 is meshed with a third-stage driven bevel gear 17 and a fourth-stage driven bevel gear 18 simultaneously; the third-stage driving wheel 13 is meshed with the fifth-stage driven bevel gear 19 and the sixth-stage driven bevel gear 20 simultaneously; the fourth-stage driving wheel 14 is meshed with the seventh-stage driven bevel gear 21 and the eighth-stage driven bevel gear 22 simultaneously, and three times of power splitting are completed.
The first-stage driven bevel gear 15, the second-stage driven bevel gear 16, the fifth-stage driven bevel gear 19 and the sixth-stage driven bevel gear 20 are simultaneously meshed with the upper bevel gear 23 of the coaxial speed reducer; the third-stage driven bevel gear 17, the fourth-stage driven bevel gear 18, the seventh-stage driven bevel gear 21 and the eighth-stage driven bevel gear 22 are simultaneously meshed with the lower bevel gear 24 of the speed change output unit, and the power converging transmission is completed;
the upper bevel gear 23 and the lower bevel gear 24 are supported back to back through the thrust bearing 25 to realize a coaxial counter-rotating function, the upper bevel gear 23 and the lower bevel gear 24 are respectively fixedly connected with the first output shaft 26 and the second output shaft 27 to realize reverse double output of power, and meanwhile, the upper bevel gear 23 and the lower bevel gear 24 are meshed with the upper tail gear 29 and the lower tail gear 30 to finish tail power output;
the upper gear 23 transmits power to the lower rotor through the first output shaft 26; the lower bevel gear 24 is fixedly connected with the sun gear 31 through the second output shaft 27 and transmits power to the planetary reduction gear; the sun gear 31 drives the planet carrier 34 to rotate through the matching relation between the planet gears 32 and the inner gear ring 33, and then the planet carrier 34 is fixedly connected with the third output shaft 28 through a spline to transmit power to the upper rotor, so that double-rotor variable speed transmission is realized;
the output shaft is a hollow shaft, and the two ends of the third output shaft 28 are provided with splines; the aperture of the first output shaft and the aperture of the second output shaft are both larger than the shaft diameter of the third output shaft, and the third output shaft passes through the centers of the first output shaft and the second output shaft and is higher than the first output shaft;
all gear axes of the torque dividing transmission unit are perpendicular to the axes of the upper and lower gears; the rotation speeds of the first output shaft and the third output shaft are unequal and the rotation directions are opposite.
In the grading speed reducer, the primary driving wheel, the secondary driven wheel and the tertiary driving wheel are all straight-tooth cylindrical gears.
The diameter of the secondary driving wheel is smaller than that of the secondary driven wheel; the upper bevel gear and the lower bevel gear have the same parameters; the diameter of the three-stage driven bevel gear is larger than that of the three-stage driving wheel.
Embodiment two:
the bevel gear configuration coaxial double-rotor speed change transmission mechanism with double engine inputs provided by the embodiment is as shown in fig. 2 and 3: the structure of the embodiment is the same as that of the first embodiment, and the difference is that the embodiment adopts double-power input, has two sets of hierarchical speed reduction devices, has the same configuration, and is symmetrically or approximately symmetrically distributed along the circumference.
As shown in fig. 3, a lower rotor 36 connected to the first output shaft 26 and an upper rotor 35 connected to the third output shaft 28 are added to the second embodiment, and the other structure is the same as that of the second embodiment.
The foregoing description of the preferred embodiments of the present invention is not intended to limit the scope of the invention, and it should be noted that modifications and variations could be made by persons skilled in the art without departing from the principles of the present invention.
Claims (6)
1. The coaxial double-rotor speed change transmission mechanism of bevel gear configuration, its characterized in that: comprises a grading speed reducer and a coaxial speed reducer; the grading speed reducer is a three-stage fixed-axis gear train consisting of I-stage gear transmission, II-stage gear transmission and III-stage gear transmission;
the I-stage gear transmission comprises a primary driving wheel and two driven face gears, and the primary driving wheel is meshed with the two driven face gears at the same time to realize primary transmission;
the II-stage gear transmission comprises two secondary driving wheels and four secondary driven wheels, wherein each secondary driving wheel is coaxial with one driven face gear and is meshed with the two secondary driven wheels at the same time, so that secondary transmission is realized;
the III-level gear transmission comprises four three-level driving wheels and eight three-level driven wheels, wherein each three-level driving wheel is coaxial with one two-level driven wheel and is meshed with two three-level driven wheels at the same time, so that three-level transmission is realized;
the coaxial speed reducer comprises an upper bevel gear, a lower bevel gear and a planetary speed change mechanism which are back to back; the upper bevel gear is meshed with the four three-stage driven wheels and fixedly connected with the first output shaft; the lower bevel gear is meshed with the other four three-stage driven wheels and is fixedly connected with the sun gear through the second output shaft to drive the planet carrier, and the planet carrier is fixedly connected with the third output shaft to finish speed change and contra-rotation double output;
the upper bevel gear and the lower bevel gear have the same parameters.
2. A bevel gear configuration coaxial twin-rotor variable speed drive according to claim 1, wherein: the upper bevel gear is also meshed with the upper tail gear, and the lower bevel gear is also meshed with the lower tail gear.
3. The bevel gear configuration coaxial dual rotor variable speed drive of claim 1 or 2, wherein: and a thrust bearing is arranged between the upper bevel gear and the lower bevel gear.
4. A bevel gear configuration coaxial dual rotor variable speed drive according to claim 3 wherein: the first output shaft, the second output shaft and the third output shaft are hollow shafts, and the two ends of the third output shaft are provided with splines; the aperture of the first output shaft and the aperture of the second output shaft are both larger than the shaft diameter of the third output shaft, and the third output shaft passes through the centers of the first output shaft and the second output shaft and is higher than the first output shaft.
5. The bevel gear configuration coaxial dual rotor variable speed drive of claim 4, wherein: the rotating speeds of the first output shaft and the third output shaft are unequal and the directions of the rotating shafts are opposite.
6. The bevel gear configuration coaxial dual rotor variable speed drive of claim 5, wherein: the number of the grading speed reducing devices is at least 1, and when multiple paths of input are adopted, each path has the same configuration and is uniformly distributed along the circumference.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010125482.9A CN111268113B (en) | 2020-02-27 | 2020-02-27 | Bevel gear configuration coaxial double-rotor speed change transmission mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010125482.9A CN111268113B (en) | 2020-02-27 | 2020-02-27 | Bevel gear configuration coaxial double-rotor speed change transmission mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN111268113A CN111268113A (en) | 2020-06-12 |
| CN111268113B true CN111268113B (en) | 2024-03-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010125482.9A Active CN111268113B (en) | 2020-02-27 | 2020-02-27 | Bevel gear configuration coaxial double-rotor speed change transmission mechanism |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113154013A (en) * | 2021-05-11 | 2021-07-23 | 中国航发沈阳发动机研究所 | Torsion-dividing output power device for central transmission bevel gear of aircraft engine |
| CN114162337B (en) * | 2021-11-27 | 2024-01-26 | 西北工业大学 | Windshield system for reducing oil injection lubrication windage loss of high-speed spiral bevel gear |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4489625A (en) * | 1982-11-23 | 1984-12-25 | Transmission Research, Inc. | Split torque transmission |
| US4811627A (en) * | 1984-08-06 | 1989-03-14 | Aerospatiale Societe Nationale Industrielle | Main transmission gearbox for a twin-engined helicopter |
| EP0753456A1 (en) * | 1995-01-04 | 1997-01-15 | Advanced Technology Institute of Commuter-Helicopter, Ltd. | Power transmission device for helicopter |
| US5807202A (en) * | 1996-09-04 | 1998-09-15 | Sikorsky Aircraft Corporation | Differential speed transmission |
| CN103979108A (en) * | 2014-05-29 | 2014-08-13 | 合肥工业大学 | Main reducer for coaxial dual-rotor high-speed helicopter with tension paddle |
| CN107559383A (en) * | 2017-07-18 | 2018-01-09 | 南京航空航天大学 | A kind of coaxial rotor transmission device with power dividing twice |
| CN211943721U (en) * | 2020-02-27 | 2020-11-17 | 西安工业大学 | Double-rotor helicopter transmission mechanism with coaxial bevel gears for double-weight splitting and converging |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7434764B2 (en) * | 2005-12-02 | 2008-10-14 | Sikorsky Aircraft Corporation | Variable speed gearbox with an independently variable speed tail rotor system for a rotary wing aircraft |
| EP2357131B1 (en) * | 2010-02-05 | 2016-09-07 | Sikorsky Aircraft Corporation | Counter rotating facegear gearbox |
-
2020
- 2020-02-27 CN CN202010125482.9A patent/CN111268113B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4489625A (en) * | 1982-11-23 | 1984-12-25 | Transmission Research, Inc. | Split torque transmission |
| US4811627A (en) * | 1984-08-06 | 1989-03-14 | Aerospatiale Societe Nationale Industrielle | Main transmission gearbox for a twin-engined helicopter |
| EP0753456A1 (en) * | 1995-01-04 | 1997-01-15 | Advanced Technology Institute of Commuter-Helicopter, Ltd. | Power transmission device for helicopter |
| US5807202A (en) * | 1996-09-04 | 1998-09-15 | Sikorsky Aircraft Corporation | Differential speed transmission |
| CN103979108A (en) * | 2014-05-29 | 2014-08-13 | 合肥工业大学 | Main reducer for coaxial dual-rotor high-speed helicopter with tension paddle |
| CN107559383A (en) * | 2017-07-18 | 2018-01-09 | 南京航空航天大学 | A kind of coaxial rotor transmission device with power dividing twice |
| CN211943721U (en) * | 2020-02-27 | 2020-11-17 | 西安工业大学 | Double-rotor helicopter transmission mechanism with coaxial bevel gears for double-weight splitting and converging |
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| CN111268113A (en) | 2020-06-12 |
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