CN114426102A - Transmission system of tilt rotorcraft - Google Patents
Transmission system of tilt rotorcraft Download PDFInfo
- Publication number
- CN114426102A CN114426102A CN202210172898.5A CN202210172898A CN114426102A CN 114426102 A CN114426102 A CN 114426102A CN 202210172898 A CN202210172898 A CN 202210172898A CN 114426102 A CN114426102 A CN 114426102A
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- rotor speed
- speed reduction
- engine
- output shaft
- rotor
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 69
- 230000009467 reduction Effects 0.000 claims abstract description 72
- 238000009434 installation Methods 0.000 claims description 3
- 239000000243 solution Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000010724 circulating oil Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 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; 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gear Transmission (AREA)
Abstract
The invention relates to a tilting rotorcraft transmission system which comprises an engine output transmission unit, a pair of rotor speed reducing units symmetrically connected to two sides of the engine output transmission unit, and a pair of tilting units symmetrically arranged on two sides of the engine output transmission unit and connected with the rotor speed reducing units in a one-to-one correspondence mode. The transmission system adopts an engine to output, carries out shunting through a bevel gear, and transmits power to the rotors at two sides, so that the centralized transmission of power input in one direction and power output in two directions is realized, the weight is greatly reduced, and the structural space is reduced; in addition, the tilting unit and the rotor speed reduction unit are arranged in the same casing, so that the weight and the structural size can be reduced.
Description
Technical Field
The invention belongs to the field of aerospace, and relates to a transmission system of a tilt rotor aircraft.
Background
In aerospace aircrafts, helicopters and fixed wing aircrafts are conventional, wherein the helicopters can take off and land vertically and hover in the air, but have low flying speed; fixed-wing aircraft have high flight speeds, but take-off requires a long runway. And the tilt rotor aircraft combines the advantages of the two aircraft types, not only can fly at high speed, but also can vertically take off and land and hover in the air. Among three key movable components of the tilt rotor aircraft, a transmission system is one of the key movable components, mainly used for driving an engine and other accessories to work, and is used for transmitting the power and the rotating speed of the engine to the rotors on two sides and other accessories according to a specific transmission ratio, so that the transmission system is an important transmission system for power output of the engine of the tilt rotor aircraft. Among the operational performance and reliability of tiltrotor aircraft, the operational performance and reliability of the transmission system play a decisive role. Because the operation requirement of the tilt rotor aircraft is special, the requirement on a transmission system of the tilt rotor aircraft is stricter; on the premise of meeting the requirements of the rotation and tilting functions of the tilting rotor, the structure of a transmission system of the tilting rotor aircraft is required to be more compact, the weight is lighter, the transmission is more reliable, the transmission efficiency is higher and the output power is more stable. In the existing tilting rotorcraft transmission system, the V-22 tilting rotorcraft is the leading foreign one, each V-22 rotor wing is provided with an independent engine drive, and two rotor wings must be provided with two engines, so that the weight is inevitably large and the structural size is large; the tilting part is driven by hydraulic pressure, and a hydraulic station must be arranged, so that the weight is increased.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a tilt-rotor aircraft transmission system, so as to solve the problems of large size, heavy weight, low efficiency, etc. of the existing transmission system under the power output functional requirement, so as to ensure compact structure, high transmission efficiency, and high reliability.
In order to achieve the purpose, the invention provides the following technical scheme:
a tilting rotorcraft transmission system comprises an engine output transmission unit, a pair of rotor speed reducing units symmetrically connected to two sides of the engine output transmission unit, and a pair of tilting units symmetrically arranged on two sides of the engine output transmission unit and connected with the rotor speed reducing units in a one-to-one correspondence manner;
the engine output transmission unit comprises an engine output shaft, an engine power reversing input bevel gear and engine power reversing output bevel gears, wherein the engine power reversing input bevel gear is arranged on the engine output shaft, and the engine power reversing output bevel gears are meshed with the engine power reversing input bevel gear and are symmetrically distributed on two sides of the engine output shaft;
each rotor speed reduction unit comprises a rotor speed reduction input shaft, a rotor speed reduction output shaft, a rotor speed reduction input bevel gear, a rotor speed reduction output bevel gear and a planetary gear train, wherein the rotor speed reduction input bevel gear and the rotor speed reduction output bevel gear are respectively and correspondingly arranged on the rotor speed reduction input shaft and the rotor speed reduction output shaft and are meshed with each other;
every unit of verting including installing the support that verts on rotor speed reduction output shaft, with vert the worm wheel output shaft that the support links to each other, install the worm wheel on the worm wheel output shaft to and the worm that meshes mutually with the worm wheel.
Furthermore, a friction clutch is mounted on an output shaft of the engine and is connected with or disconnected from the engine through the friction clutch.
Further, the worm is connected to a motor.
Further, the worm is connected with the motor through a coupler.
Furthermore, an output shaft of the engine is in interference fit or spline connection with a power reversing input bevel gear of the engine, and a surface-to-surface mounting type tapered roller bearing is mounted on the output shaft of the engine to provide support.
Furthermore, an integrated structure is adopted between the rotor speed reduction input shaft and the corresponding engine reversing output bevel gear, the integrated structure is in interference fit or spline connection with the rotor speed reduction input bevel gear, and back-to-back installation type tapered roller bearings are installed on the rotor speed reduction input shaft to provide support.
Furthermore, the rotor speed reduction output shaft is in interference fit or spline connection with a rotor speed reduction output bevel gear and is in spline connection with a planetary gear train, and a surface-to-surface mounting type tapered roller bearing is mounted on the rotor speed reduction output shaft to provide support.
Furthermore, the planetary gear train is connected to the rotor through the rotor shaft, the planetary gear train is in spline connection with the rotor shaft, and back-to-back installation type tapered roller bearings are installed on the rotor shaft to provide support.
Further, the worm adopts deep groove ball bearing in order to support, and the worm wheel adopts deep groove ball bearing to support on the worm wheel output shaft, and the support that verts adopts deep groove ball bearing to support on rotor speed reduction output shaft.
Furthermore, the tilting bracket drives the rotor speed reduction output shaft to tilt within the range of 0-110 degrees.
The invention has the beneficial effects that:
1. the tilting rotorcraft transmission system disclosed by the invention adopts an engine to output, carries out shunting through the bevel gear, and transmits power to the rotors on two sides, so that the power input in one direction and the power output in two directions are realized in centralized transmission, the weight is greatly reduced, and the structural space is reduced; in addition, the tilting unit and the rotor speed reduction unit are arranged in the same casing, so that the weight and the structural size can be reduced.
2. The tilting rotor aircraft transmission system disclosed by the invention adopts two-stage bevel gear pairs and one-stage planetary gear train, the bevel gear pairs carry out micro-deceleration and reversing, the planetary gear train has compact structure, can realize large transmission ratio and carry out large deceleration, and has the advantages of few transmission stages, compact structure and high transmission efficiency.
3. According to the transmission system of the tilt rotor aircraft disclosed by the invention, one end of a worm is connected with a motor, a worm wheel drives a tilt bracket, and the tilt bracket drives a rotor to tilt at an angle of 0-110 degrees. The worm gear has a self-locking function, and can prevent reversion caused by external force.
4. According to the tilting rotor aircraft transmission system disclosed by the invention, the power of the engine is transmitted into the whole system through the friction clutch, so that the on-off of power transmission can be effectively controlled.
5. According to the tilting rotorcraft transmission system disclosed by the invention, the engine output shaft and the engine power reversing input bevel gear are supported by a face-to-face mounting type tapered roller bearing, the back-to-back tapered roller bearing is adopted between the rotor speed reduction input shaft and the engine reversing output bevel gear for supporting, the back-to-back tapered roller bearing is adopted between the rotor speed reduction input shaft and the rotor speed reduction input bevel gear for supporting, the face-to-face tapered roller bearing is adopted between the rotor speed reduction output shaft and the rotor speed reduction output bevel gear for supporting, so that the axial force generated by the bevel gear meshing of the transmission system can be offset, and the dislocation quantity can be reduced; the stability of transmission is also improved, and the transmission is more stable.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims thereof.
Drawings
For the purposes of promoting a better understanding of the objects, aspects and advantages of the invention, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings in which:
FIG. 1 is a schematic structural view of a tiltrotor aircraft transmission system according to the present invention;
fig. 2 is a front view of the tiltrotor aircraft transmission system of the present invention;
FIG. 3 is a schematic view of a worm and gear configuration of a tiltrotor aircraft transmission system according to the present invention;
fig. 4 is a schematic drive diagram of a tiltrotor aircraft drive system according to the present invention.
Reference numerals: the engine-driven generator comprises an engine output shaft 1, an engine power reversing input bevel gear 3, an engine power reversing output bevel gear 4, a rotor speed reducing input shaft 7, a rotor speed reducing input bevel gear 11, a rotor speed reducing output bevel gear 12, a planetary gear train 14, a rotor shaft 15, a rotor speed reducing output shaft 16, a tilting bracket 19, a worm wheel 20, a worm 21, a worm wheel output shaft 24, tapered roller bearings 2, 5, 6, 8, 9, 10, 13, 18, 25 and 26, deep groove ball bearings 17, 22 and 23 and a friction clutch 27.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention in a schematic way, and the features in the following embodiments and examples may be combined with each other without conflict.
Wherein the showings are for the purpose of illustrating the invention only and not for the purpose of limiting the same, and in which there is shown by way of illustration only and not in the drawings in which there is no intention to limit the invention thereto; to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
The same or similar reference numerals in the drawings of the embodiments of the present invention correspond to the same or similar components; in the description of the present invention, it should be understood that if there is an orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "front", "rear", etc., based on the orientation or positional relationship shown in the drawings, it is only for convenience of description and simplification of description, but it is not an indication or suggestion that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes, and are not to be construed as limiting the present invention, and the specific meaning of the terms may be understood by those skilled in the art according to specific situations.
Referring to fig. 1 to 4, a tilt rotorcraft transmission system includes an engine output transmission unit, a pair of rotor speed reduction units symmetrically connected to two sides of the engine output transmission unit, and a pair of tilt units symmetrically disposed on two sides of the engine output transmission unit and connected to the rotor speed reduction units in a one-to-one correspondence;
the engine output transmission unit comprises an engine output shaft 1, an engine power reversing input bevel gear 3 arranged on the engine output shaft 1, and engine power reversing output bevel gears 4 which are meshed with the engine power reversing input bevel gear 3 and symmetrically distributed on two sides of the engine output shaft 1; the friction clutch 27 is arranged on the output shaft 1 of the engine, the friction clutch 27 is connected with or disconnected from the engine, the power of the engine is transmitted into the whole system through the friction clutch 27, and the on-off of power transmission can be effectively controlled. An engine output shaft 1 is in interference fit or spline connection with an engine power reversing input bevel gear 3, and surface-to-surface mounting type tapered roller bearings 2 and 8 are mounted on the engine output shaft 1 to provide support.
Each rotor speed reduction unit comprises a rotor speed reduction input shaft 7, a rotor speed reduction output shaft 16, a rotor speed reduction input bevel gear 11 and a rotor speed reduction output bevel gear 12 which are respectively and correspondingly arranged on the rotor speed reduction input shaft 7 and the rotor speed reduction output shaft 16 and are meshed with each other, and a planetary gear train 14 arranged on the rotor speed reduction output shaft 16; the planetary gear train 14 is connected to the rotor through a rotor shaft 15, the planetary gear train 14 is in spline connection with the rotor shaft 15, and two back-to-back mounting type tapered roller bearings 25 and 26 are mounted on the rotor shaft 15 to provide support. The rotor speed reduction input shaft 7 and the corresponding engine reversing output bevel gear are in an integrated structure and are in interference fit or spline connection with the rotor speed reduction input bevel gear 11, and four back-to-back mounting type tapered roller bearings 5, 6, 9 and 10 are mounted on the rotor speed reduction input shaft 7 to provide support. The rotor reduction output shaft 16 is in interference or splined engagement with the rotor reduction output bevel gear 12, and is splined to the planetary gear train 14, on which face-to-face mounted tapered roller bearings 13, 18 are mounted to provide support.
Each tilting unit includes a tilting bracket 19 mounted on the rotor speed reduction output shaft 16, a worm wheel output shaft 24 connected to the tilting bracket 19, a worm wheel 20 mounted on the worm wheel output shaft 24, and a worm 21 engaged with the worm wheel 20. The worm 21 is connected to the motor through a coupling. Worm 21 adopts two deep groove ball bearings 22 in order to support, and worm wheel 20 adopts two deep groove ball bearings 23 to support on worm wheel output shaft 24, and tilting bracket 19 adopts two deep groove ball bearings 17 to support on rotor speed reduction output shaft 16.
The transmission system adopts a two-stage bevel gear train and a one-stage planetary gear train, namely, an engine power reversing input bevel gear 3 is meshed with an engine power reversing output bevel gear 4 to form an engine power reversing bevel gear pair; the rotor speed reduction input bevel gear 11 is meshed with the rotor speed reduction output bevel gear 12 to form a rotor speed reduction bevel gear pair; the rotor power input planetary gear train 14; the tilting reversing power input worm 21 is meshed with the tilting power output worm wheel 20 to form a worm gear pair; after the power is output by the engine, the power is connected with a friction clutch 27 on the power output shaft 1 of the engine, the friction clutch 27 is engaged, the power is transmitted to the power output shaft 1 of the engine, and the left rotor wing and the right rotor wing are respectively driven through two paths; the first power transmission route is transmitted to an engine power reversing bevel gear pair through an engine power output shaft 1, then the power is transmitted to a rotor speed reducing output bevel gear pair through a rotor speed reducing input shaft 7, and then the power is transmitted to a planetary gear train 14 through a rotor speed reducing output shaft 16, so that a rotor (not shown) is driven; the second transmission route is the same as the first transmission route; the power transmission route of verting drives the worm gear pair by motor (not shown), with power transmission to the support of verting, and then can vert the rotor as required 0-110. The invention is that an engine drives the rotor wings on both sides to rotate, the tilting unit and the rotor wing deceleration unit can be put in the same casing, when realizing the rotation and tilting of the rotor wings on both sides, the invention has the advantages of compact structure, low weight, high efficiency and good stability.
When the power-assisted steering device works, power is input from an engine output shaft 1, the engine output shaft 1 is in interference fit or spline connection with an engine power reversing input bevel gear 3 and drives engine power reversing output bevel gears 4 on two sides to rotate; the engine power reversing output bevel gear 4 and the rotor speed reduction input shaft 7 adopt an integrated structure; the rotor speed reduction input shaft 7 is connected with the rotor speed reduction number input bevel gear 11 by a spline or interference fit and drives the rotor speed reduction output bevel gear 12 to rotate; the rotor speed reduction output bevel gear 12 is connected with the rotor speed reduction output shaft 16 by adopting a spline or interference; in addition, the rotor speed reduction output shaft 16 is connected with a sun gear of the planetary gear train 14 through a spline and drives the planetary gear train 14 to rotate; the planetary gear train 14 is connected with the rotor shaft 15 through a spline, and drives the rotor shaft 15 to rotate, so as to output power.
When tilting, power is connected with the worm 21 through a coupler by a motor (not shown), the power is transmitted to the worm 21, the worm 21 is meshed with the worm wheel 20, the power is transmitted to the tilting bracket 19, and the tilting bracket 19 drives the rotor speed reduction output shaft 16 to tilt within the range of 0-110 degrees.
In specific implementation, the reduction gearbox where the engine output shaft 1 is located and the reduction gearbox where the rotor speed reduction output shaft 16 is located are lubricated by adopting circulating oil injection, and a heat dissipation system is arranged outside the reduction gearbox.
Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered by the claims of the present invention.
Claims (10)
1. A tiltrotor aircraft transmission system, characterized by: the system comprises an engine output transmission unit, a pair of rotor speed reducing units symmetrically connected to two sides of the engine output transmission unit, and a pair of tilting units symmetrically arranged on two sides of the engine output transmission unit and connected with the rotor speed reducing units in a one-to-one correspondence manner;
the engine output transmission unit comprises an engine output shaft, an engine power reversing input bevel gear and engine power reversing output bevel gears, wherein the engine power reversing input bevel gear is arranged on the engine output shaft, and the engine power reversing output bevel gears are meshed with the engine power reversing input bevel gear and are symmetrically distributed on two sides of the engine output shaft;
each rotor speed reduction unit comprises a rotor speed reduction input shaft, a rotor speed reduction output shaft, a rotor speed reduction input bevel gear, a rotor speed reduction output bevel gear and a planetary gear train, wherein the rotor speed reduction input bevel gear and the rotor speed reduction output bevel gear are respectively and correspondingly arranged on the rotor speed reduction input shaft and the rotor speed reduction output shaft and are meshed with each other;
every unit of verting including installing the support that verts on rotor speed reduction output shaft, with vert the worm wheel output shaft that the support links to each other, install the worm wheel on the worm wheel output shaft to and the worm that meshes mutually with the worm wheel.
2. The tiltrotor aircraft transmission system according to claim 1, wherein: and a friction clutch is mounted on the output shaft of the engine and is connected with or disconnected from the engine through the friction clutch.
3. The tiltrotor aircraft transmission system according to claim 1, wherein: the worm is connected to a motor.
4. The tiltrotor aircraft transmission system according to claim 3, wherein: the worm is connected with the motor through a coupler.
5. The tiltrotor aircraft transmission system according to claim 1, wherein: the engine output shaft is in interference fit or spline connection with the engine power reversing input bevel gear, and a surface-to-surface mounting type tapered roller bearing is mounted on the engine output shaft to provide support.
6. The tiltrotor aircraft transmission system according to claim 1, wherein: the speed-reducing input shaft of the rotor wing and the corresponding reversing output bevel gear of the engine adopt an integrated structure and are in interference fit or spline connection with the speed-reducing input bevel gear of the rotor wing, and back-to-back mounting type tapered roller bearings are mounted on the speed-reducing input shaft of the rotor wing to provide support.
7. The tiltrotor aircraft transmission system according to claim 1, wherein: the rotor speed reduction output shaft is in interference fit or spline connection with a rotor speed reduction output bevel gear and is in spline connection with a planetary gear train, and a surface-to-surface mounting type tapered roller bearing is mounted on the rotor speed reduction output shaft to provide support.
8. The tiltrotor aircraft transmission system according to claim 1, wherein: the planetary gear train is connected to the rotor through the rotor shaft, and planetary gear train and rotor shaft spline connection are installed back to back installation formula tapered roller bearing in order to provide the support on the rotor shaft.
9. The tiltrotor aircraft transmission system according to claim 1, wherein: the worm adopts deep groove ball bearing in order to support, and the worm wheel adopts deep groove ball bearing to support on the worm wheel output shaft, and the support that verts adopts deep groove ball bearing to support on rotor speed reduction output shaft.
10. The tiltrotor aircraft transmission system according to claim 1, wherein: the tilting bracket drives the rotor speed reduction output shaft to tilt within the range of 0-110 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210172898.5A CN114426102A (en) | 2022-02-24 | 2022-02-24 | Transmission system of tilt rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210172898.5A CN114426102A (en) | 2022-02-24 | 2022-02-24 | Transmission system of tilt rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114426102A true CN114426102A (en) | 2022-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210172898.5A Pending CN114426102A (en) | 2022-02-24 | 2022-02-24 | Transmission system of tilt rotorcraft |
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| Country | Link |
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| CN (1) | CN114426102A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115432181A (en) * | 2022-10-08 | 2022-12-06 | 重庆大学 | Tilt-rotor aircraft transmission system with coaxial input shaft and rotor shaft |
| CN115771614A (en) * | 2023-02-14 | 2023-03-10 | 江苏新扬新材料股份有限公司 | Large-scale rotorcraft transmission system that verts |
| WO2024191152A1 (en) * | 2023-03-16 | 2024-09-19 | 송길봉 | Aircraft using force couple |
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| US3623682A (en) * | 1968-09-27 | 1971-11-30 | Giraviens Dorand | Rotary wing aircraft |
| CN101973398A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft |
| CN106976552A (en) * | 2017-03-17 | 2017-07-25 | 沈阳无距科技有限公司 | Tilting rotor wing unmanned aerial vehicle |
| US20180155019A1 (en) * | 2016-11-28 | 2018-06-07 | Korea Aerospace Research Institute | Tilt-prop aircraft |
| CN109533312A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of transmission device that verts that engine is fixed |
| CN110920912A (en) * | 2019-11-29 | 2020-03-27 | 重庆大学 | High-speed helicopter transmission system |
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2022
- 2022-02-24 CN CN202210172898.5A patent/CN114426102A/en active Pending
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| US3623682A (en) * | 1968-09-27 | 1971-11-30 | Giraviens Dorand | Rotary wing aircraft |
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| US20180155019A1 (en) * | 2016-11-28 | 2018-06-07 | Korea Aerospace Research Institute | Tilt-prop aircraft |
| CN106976552A (en) * | 2017-03-17 | 2017-07-25 | 沈阳无距科技有限公司 | Tilting rotor wing unmanned aerial vehicle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115432181A (en) * | 2022-10-08 | 2022-12-06 | 重庆大学 | Tilt-rotor aircraft transmission system with coaxial input shaft and rotor shaft |
| CN115432181B (en) * | 2022-10-08 | 2024-04-19 | 重庆大学 | Tilt gyroplane transmission system with input shaft coaxial with rotor shaft |
| CN115771614A (en) * | 2023-02-14 | 2023-03-10 | 江苏新扬新材料股份有限公司 | Large-scale rotorcraft transmission system that verts |
| WO2024191152A1 (en) * | 2023-03-16 | 2024-09-19 | 송길봉 | Aircraft using force couple |
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