CN112555363A - Helicopter rotor two-stage speed change system and method - Google Patents
Helicopter rotor two-stage speed change system and method Download PDFInfo
- Publication number
- CN112555363A CN112555363A CN202011262020.8A CN202011262020A CN112555363A CN 112555363 A CN112555363 A CN 112555363A CN 202011262020 A CN202011262020 A CN 202011262020A CN 112555363 A CN112555363 A CN 112555363A
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- gear
- speed change
- planet carrier
- helicopter rotor
- controllable
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000001105 regulatory effect Effects 0.000 claims abstract description 13
- 230000005540 biological transmission Effects 0.000 description 24
- 238000010586 diagram Methods 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
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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
- F16H3/00—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion
- F16H3/44—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structure Of Transmissions (AREA)
Abstract
The invention discloses a two-stage speed change system and a two-stage speed change method for a helicopter rotor wing, wherein the system comprises an overrunning clutch, a first controllable clutch, a speed regulating gear, a driving gear, a lower duplicate gear, a planet gear, an upper duplicate gear, a second controllable brake and a planet carrier; the gears are all bevel gears; the upper duplicate gear and the lower duplicate gear are coaxially arranged and are supported on the planet carrier through bearings, and the upper duplicate gear is connected with the supporting component through a second controllable brake; the horizontal power input shaft is connected with a driving gear through an overrunning clutch, and the speed regulating gear is connected with the driving gear shaft through a controllable clutch; the driving gear is meshed with a lower bevel gear of the lower duplicate gear, and an upper bevel gear of the lower duplicate gear is meshed with the planet gear; the planet gear is meshed with a lower bevel gear of the upper duplicate gear, and an upper bevel gear of the upper duplicate gear is meshed with the speed regulating gear; a rotating shaft of the planet gear is connected with the planet carrier; the upper end of the planet carrier is used as an output end. The method realizes two-stage speed change of the helicopter rotor wing through two control actuators.
Description
Technical Field
The invention belongs to the field of helicopter rotor transmission, and particularly relates to a two-stage speed change system and a two-stage speed change method for a helicopter rotor.
Background
The optimal rotating speeds of the rotors of the helicopter are different under different flight working conditions, and a transmission system is generally required to have speed change capability in order to reduce the oil consumption of the helicopter and improve the cruising ability of the helicopter. The existing speed change system mostly adopts straight-tooth planet gears for transmission, for example, cn201410066639.x (a variable speed transmission system for an unmanned aerial vehicle) discloses a two-stage speed change system, which realizes the purpose of changing a transmission route by controlling the on-off of a friction clutch and a brake arranged in a conventional cylindrical gear planet transmission system in a matching manner, thereby realizing the switching of rotating speeds. Cn202010113511.x (a variable speed transmission system and unmanned aerial vehicle) discloses a similar two-stage speed change system, which also utilizes conventional cylindrical gear planetary transmission, and combines the mutual cooperation of an overrunning clutch and a friction clutch to realize the purpose of speed change.
The two-stage speed change systems disclosed in the two patents are both in conventional cylindrical gear planetary transmission, the power input shaft and the output shaft of the speed change component are arranged in parallel, the power input shaft and the output shaft are inconsistent with the transmission layout of horizontal input and vertical output required by a common helicopter, and a corresponding reversing transmission device needs to be additionally arranged, so that the whole speed change system is large in size.
In addition, because the conventional cylindrical gear is adopted for planetary transmission, a fixed gear ring with a larger size needs to be processed, the fixed gear ring deforms greatly in the processing and heat treatment processes, so that the condition of uneven load exists in the actual use process of the planetary gear, the unbalanced load of a transmission system is caused, the transmission efficiency and the transmission service life are influenced, and even the flight safety is influenced.
Disclosure of Invention
The invention aims to provide a two-stage speed change system and a two-stage speed change method for a helicopter rotor wing, so as to realize two-stage speed change of the helicopter rotor wing.
The technical solution for realizing the purpose of the invention is as follows:
a two-stage speed change system of a helicopter rotor wing comprises an overrunning clutch, a first controllable clutch, a speed regulating gear, a driving gear, a lower duplicate gear, a planet gear, an upper duplicate gear, a second controllable brake and a planet carrier; the gears are all bevel gears;
the upper duplicate gear and the lower duplicate gear are coaxially arranged and are supported on the planet carrier through bearings, and the upper duplicate gear is connected with the supporting component through a second controllable brake;
the horizontal power input shaft is connected with a driving gear through an overrunning clutch, and the speed regulating gear is connected with the driving gear shaft through a controllable clutch;
the driving gear is meshed with a lower bevel gear of the lower duplicate gear, an upper bevel gear of the lower duplicate gear is meshed with a planet gear, the planet gear is meshed with a lower bevel gear of the upper duplicate gear, and an upper bevel gear of the upper duplicate gear is meshed with the speed regulating gear; a rotating shaft of the planet gear is connected with the planet carrier; the upper end of the planet carrier is used as an output end and is used for connecting a helicopter rotor.
A two-stage speed change method of a helicopter rotor comprises the following steps:
when the first controllable clutch is disconnected and the second controllable brake is in a braking condition, the planet carrier outputs a first rotating speed;
and when the first controllable clutch is engaged and the second controllable brake is not braking, the planet carrier outputs the second rotating speed.
Compared with the prior art, the invention has the following remarkable advantages:
(1) the two-stage speed change method disclosed by the invention directly changes the power input in the horizontal direction to the power output in the vertical direction, more meets the transmission requirements of the horizontal input and the vertical output of a common helicopter, and realizes the two-stage speed change requirements based on the bevel gear transmission and the planetary transmission structure for engaging the controllable clutch and the controllable actuator.
(2) The invention is realized by adopting the bevel gears, each gear can be ground, the transmission precision is high, and the problem of uniform loading of the planet gears can be effectively solved.
(3) The overrunning clutch can protect the rotor wing from reversely driving the engine, all gears adopt bevel gears, and under the condition of the same power requirement, the engine has small geometric dimension, compact structure and high system integration level.
Drawings
Fig. 1 is a mechanical diagram of the overall architecture of a two-stage speed change system of a helicopter rotor.
Fig. 2 is a mechanical schematic diagram of the lower duplicate gear structure.
Fig. 3 is a mechanical schematic diagram of the upper duplicate gear structure.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
The two-stage speed change system of the helicopter rotor wing comprises an overrunning clutch 1, a first controllable clutch 2, a speed regulating gear 3, a driving gear 4, a lower duplicate gear 5, a planet gear 6, an upper duplicate gear 7, a second controllable brake 8 and a planet carrier 9; the gears are all bevel gears (straight bevel gears or spiral bevel gears can be adopted); the upper duplicate gear 7 and the lower duplicate gear 5 are coaxially arranged and are supported on a planet carrier 9 through bearings, and the upper duplicate gear 7 is connected with a supporting component through a second controllable brake 8; the horizontal power input shaft is connected with a driving gear 4 through an overrunning clutch 1, and a speed regulating gear 3 is connected with a supporting shaft of the driving gear 4 through a controllable clutch 2; the driving gear 4 is meshed with a lower bevel gear 5-1 of the lower duplicate gear 5, an upper bevel gear 5-2 planet gear 6 of the lower duplicate gear 5 is meshed with a lower bevel gear 7-2 of the upper duplicate gear 7, and an upper bevel gear 7-1 of the upper duplicate gear 7 is meshed with the speed regulating gear 3; the rotating shaft of the planet wheel 6 is connected with a planet carrier 9, the rotating axis of the planet carrier 9 is in the vertical direction, the upper end of the planet carrier is used as an output end, and the output end is connected with a helicopter rotor wing; the revolution axis of the planet wheel 6 is parallel to the rotation axis of the planet carrier 9, and the rotation axis of the planet wheel 6 is perpendicular to the rotation axis of the planet carrier 9; the lower duplicate gear 5, the planet gear 6, the upper duplicate gear 7 and the planet carrier 9 form a planet transmission mechanism, the mechanism is output by the planet carrier 9, and the rotating speed of the planet carrier 9 is determined by the rotating speeds of the lower duplicate gear 5 and the upper duplicate gear 7.
The method for realizing the two-stage speed change of the helicopter rotor by the two-stage speed change system of the helicopter rotor comprises the following steps:
when the first controllable clutch 2 is disconnected and the second controllable brake 8 is braked, the upper duplex gear 7 and the casing of the speed change system are attracted and are kept still, the speed regulation gear 3 does not have power input and also keeps a static state, the horizontal power input shaft inputs power through the driving gear 4 to drive the lower duplex gear 5 to rotate, and the planet carrier 9 outputs a first rotating speed.
When the first controllable clutch 2 is engaged and the second controllable brake 8 is not braking, the horizontal power input shaft drives the lower duplicate gear 5 to rotate through the driving gear 4, and simultaneously the speed regulating gear 3 drives the upper duplicate gear 7 to rotate at a fixed rotating speed, and at the moment, the planet carrier 9 outputs a second rotating speed.
The two-stage speed change method disclosed by the invention directly changes the power input in the horizontal direction to the power output in the vertical direction, and more meets the transmission requirements of the horizontal input and the vertical output of a common helicopter. The conventional planetary variable-speed transmission adopts cylindrical gear transmission, and a fixed gear ring in the conventional planetary variable-speed transmission has larger deformation in the machining process, so that the condition of uneven load of the planetary gear in the actual use process exists.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011262020.8A CN112555363B (en) | 2020-11-12 | 2020-11-12 | Helicopter rotor wing two-stage speed change system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011262020.8A CN112555363B (en) | 2020-11-12 | 2020-11-12 | Helicopter rotor wing two-stage speed change system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112555363A true CN112555363A (en) | 2021-03-26 |
| CN112555363B CN112555363B (en) | 2023-08-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011262020.8A Active CN112555363B (en) | 2020-11-12 | 2020-11-12 | Helicopter rotor wing two-stage speed change system and method |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110053727A1 (en) * | 2009-08-31 | 2011-03-03 | Hong Fu Jin Precision Industry(Shenzhen) Co., Ltd. | Planetary gear transmission mechanism |
| CN103770936A (en) * | 2014-02-08 | 2014-05-07 | 合肥工业大学 | Helical bevel gear planetary gear train for main reducing gear of helicopter |
| CN206130026U (en) * | 2016-09-09 | 2017-04-26 | 广州富士汽车整线集成有限公司 | Electric motor car automatic gearbox |
| CN108412981A (en) * | 2018-04-19 | 2018-08-17 | 广东机电职业技术学院 | A kind of planet gear type differential mechanism |
| CN110030356A (en) * | 2019-04-23 | 2019-07-19 | 合肥工业大学 | A kind of third gear electric car automatic speed transmission based on bevel gear |
-
2020
- 2020-11-12 CN CN202011262020.8A patent/CN112555363B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110053727A1 (en) * | 2009-08-31 | 2011-03-03 | Hong Fu Jin Precision Industry(Shenzhen) Co., Ltd. | Planetary gear transmission mechanism |
| CN103770936A (en) * | 2014-02-08 | 2014-05-07 | 合肥工业大学 | Helical bevel gear planetary gear train for main reducing gear of helicopter |
| CN206130026U (en) * | 2016-09-09 | 2017-04-26 | 广州富士汽车整线集成有限公司 | Electric motor car automatic gearbox |
| CN108412981A (en) * | 2018-04-19 | 2018-08-17 | 广东机电职业技术学院 | A kind of planet gear type differential mechanism |
| CN110030356A (en) * | 2019-04-23 | 2019-07-19 | 合肥工业大学 | A kind of third gear electric car automatic speed transmission based on bevel gear |
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| Publication number | Publication date |
|---|---|
| CN112555363B (en) | 2023-08-04 |
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Address after: No.2, Huangpu Road, Xuanwu District, Nanjing, Jiangsu Province, 210016 Patentee after: China Rongtong Group 60th Research Institute Country or region after: China Address before: No. 2 Huangpu Road, Xuanwu District, Nanjing City, Jiangsu Province Patentee before: NO.60 INSTITUTE OF THE HEADQUARTERS OF GENERAL STAFF OF PLA Country or region before: China |
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