CN110615094A - Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system - Google Patents
Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system Download PDFInfo
- Publication number
- CN110615094A CN110615094A CN201811539141.5A CN201811539141A CN110615094A CN 110615094 A CN110615094 A CN 110615094A CN 201811539141 A CN201811539141 A CN 201811539141A CN 110615094 A CN110615094 A CN 110615094A
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- CN
- China
- Prior art keywords
- transmission shaft
- transmission
- transfer case
- hub sleeve
- shaft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
Abstract
A multi-shaft multi-directional tilting type multi-rotor aircraft transmission system comprises an engine (1), a first transfer case (2), a second transfer case (3), a third transfer case (4), a rotor tilting device (5) and a transmission shaft tilting device (6), wherein four first transmission shaft arms (10) are symmetrically arranged on the first transfer case (2) in a cross manner, first transmission shafts (11) are respectively arranged in the four first transmission shaft arms (10), and an output shaft of the engine (1) drives the four first transmission shafts (11) to rotate through gears of the first transfer case (2); the output end of the first transmission shaft arm (10) is provided with a second transfer case (3), the second transfer case (3) is symmetrically provided with two second transmission shaft arms (20), and the two second transmission shaft arms (20) are internally provided with second transmission shafts (21) respectively.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a transmission system of a multi-shaft multi-directional tilting type multi-rotor aircraft.
Background
At present, the rotor helicopter or the rotor unmanned aerial vehicle can be applied to low-airspace flight aspects such as rescue and emergency rescue, delivery and transportation, reconnaissance and aerial photography and the like, can vertically take off and land, and accurately hover above a specific position to perform necessary work, most of the main rotor aircrafts are designed by driving one rotor wing by using one power device to provide flight lift force for the aircrafts, and the single-rotor, multi-rotor and tilt rotor aircrafts are the same; the single-rotor aircraft is generally a fuel oil power driven helicopter, the propeller blades of the single-rotor aircraft are long, the takeoff weight is large, but the part of the downward airflow generated by the rotor wing is blocked by the aircraft body, the energy consumption is high, the stability and the safety are not high, the takeoff is often limited by conditions such as a plurality of climates, environments and the like, and once the rotor wing or the power fails, the aircraft is damaged and people die; and many rotor crafts use on small-size unmanned aerial vehicle more, every rotor drives with a power device, mostly be electric drive, and can not realize that the rotor verts, electric power duration is limited, still can't transport the heavy weight goods, many rotor crafts are more stable than single rotor craft flight, safer, more energy-conserving, control more nimble, use more extensively, however, it is a blank to drive many rotor multi-angle with a power device on the market and vert and can do many gesture nimble many rotor crafts that fly to control.
Disclosure of Invention
The present invention is directed to a multi-shaft multi-directional tilting multi-rotor aircraft transmission system.
The invention comprises an engine, a first transfer case, a second transfer case, a third transfer case, a rotor wing tilting device and a transmission shaft tilting device, wherein four first transmission shaft arms are symmetrically arranged on the first transfer case in a cross manner, first transmission shafts are respectively arranged in the four first transmission shaft arms, and an output shaft of the engine drives the four first transmission shafts to rotate through a first transfer case gear; the output end of the first transfer case arm is provided with a second transfer case, the second transfer case is symmetrically provided with two second transfer case arms, second transmission shafts are respectively arranged in the two second transfer case arms, and the output end of the first transmission shaft drives the two second transmission shafts to rotate through a second transfer case gear; the output end of the second transmission shaft arm is provided with a third transfer case, the third transfer case is provided with a third transmission shaft arm, a third transmission shaft is arranged in the third transmission shaft arm, the output end of the second transmission shaft drives the third transmission shaft to rotate through a third transfer case gear, the output end of the third transmission shaft is provided with a rotor wing tilting device, the rotor wing tilting device comprises a hub sleeve, a pair of blades and four hub sleeve control hydraulic cylinders, the pair of blades are symmetrically arranged at the top of the hub sleeve, one end, close to the top, in the hub sleeve is connected with the third transmission shaft through a universal coupling, one end of the universal coupling is fixedly connected in the hub sleeve, the other end of the universal coupling is fixedly connected on the third transmission shaft, one end, close to the bottom, in the hub sleeve is connected with the third transmission shaft arm through the four hub sleeve control hydraulic cylinders, the four hub sleeve control hydraulic cylinders are symmetrically arranged on the, a piston rod of the propeller hub sleeve control hydraulic cylinder is provided with a spring buffer, one end of the spring buffer is provided with a roller and is movably matched with the inner wall of the propeller hub sleeve through the roller, four auxiliary balance spring buffers are symmetrically arranged on a third transmission shaft arm above the propeller hub sleeve control hydraulic cylinder in a cross manner, one end of each auxiliary balance spring buffer is provided with a roller and is movably matched with the inner wall of the propeller hub sleeve through the roller; second transfer case and first transmission shaft arm link up the department and are equipped with the transmission shaft device of verting, the transmission shaft device of verting includes toothed disc and toothed disc driving motor, the second transfer case passes through axle sleeve movable mounting on first transmission shaft arm, toothed disc fixed mounting is on the axle sleeve of second transfer case, toothed disc driving motor's output is equipped with the drive gear who uses with the toothed disc cooperation, toothed disc driving motor fixed mounting is on first transmission shaft arm to use first transmission shaft arm to rotate as the axle center through gear drive second transfer case.
The output shaft of the engine, the first transmission shaft, the second transmission shaft and the third transmission shaft are all transmitted through conical gears, four conical gears which are distributed in a cross shape are arranged in the first transfer box, two adjacent conical gears are meshed with each other, the four conical gears which are distributed in the cross shape correspond to the four first transmission shafts respectively, coaxial first transmission conical large gears are further arranged on two opposite first transmission shafts, and a main transmission conical gear which is matched with the two first transmission conical large gears for use is arranged on the output shaft of the engine; three bevel gears are distributed in the second transfer case in a T shape, the three bevel gears respectively correspond to the output end of the first transmission shaft and the input ends of the two second transmission shafts, and the bevel gear at the output end of the first transmission shaft drives the bevel gears at the input ends of the other two second transmission shafts to rotate; two bevel gears are arranged in the third transfer case for transmission, wherein one bevel gear corresponds to the output end of the second transmission shaft, and the other bevel gear corresponds to the input end of the third transmission shaft.
Still be equipped with the electromagnetism gag lever post on the first transmission shaft arm, it has the spacing hole of using with the cooperation of electromagnetism gag lever post to open on the gear disc of transmission shaft tilting device.
The invention has the advantages that: the invention can realize vertical take-off and landing of the gyroplane, and has the advantages of flexibility, maneuverability, stability and the like of the tilt gyroplane and the multi-rotor unmanned plane; the method for changing the inclination angle of the rotor wing is completed in the hub sleeve, and compared with the pull rod type control inclined rotor wing of the traditional rotor wing aircraft, the method is safer and has smaller wind resistance; the multidirectional tilting device of the transmission shaft is ingenious in design, wide in adaptability to flight working conditions, high in flight efficiency and energy-saving, two tilting modes are matched for use, and multi-dimensional high-flexibility multi-attitude control flight can be realized.
Description of the drawings
FIG. 1 is a schematic diagram of the present invention.
Fig. 2 is a schematic view of the gearing of the various drive shafts of the present invention.
Figure 3 is a schematic view of a rotor tilter assembly according to the present invention.
Fig. 4 is a schematic structural view of a transmission shaft tilting device of the present invention.
FIG. 5 is a schematic representation of the internal gear drive of the first transfer case of the present invention.
Fig. 6 is an exploded view of the gear assembly of fig. 5 of the present invention.
Fig. 7 is a schematic illustration of the tilt position of the lift flight drive shaft of the present invention.
Fig. 8 is a schematic view of the forward flight drive shaft tilt position of the present invention.
Fig. 9 is a schematic illustration of the reverse flight drive shaft tilt position of the present invention.
Fig. 10 is a schematic view of the right flight drive shaft tilt position of the present invention.
Fig. 11 is a schematic illustration of the leftward flight drive shaft tilt position of the present invention.
Figure 12 is a schematic view of a counter-clockwise flying rotor tilt position of the present invention.
Figure 13 is a schematic view of the clockwise flight rotor tilt position of the present invention.
Detailed Description
As shown in the attached drawings, the invention comprises an engine 1, a first transfer case 2, a second transfer case 3, a third transfer case 4, a rotor wing tilting device 5 and a transmission shaft tilting device 6, wherein four first transmission shaft arms 10 are symmetrically arranged on the first transfer case 2 in a cross manner, first transmission shafts 11 are respectively arranged in the four first transmission shaft arms 10, and an output shaft of the engine 1 drives the four first transmission shafts 11 to rotate through gears of the first transfer case 2; the output end of the first transfer shaft arm 10 is provided with a second transfer case 3, the second transfer case 3 is symmetrically provided with two second transfer shaft arms 20, second transmission shafts 21 are respectively arranged in the two second transfer shaft arms 20, and the output end of the first transmission shaft 11 drives the two second transmission shafts 21 to rotate through a gear of the second transfer case 3; the output end of the second transmission shaft arm 20 is provided with a third transfer case 4, the third transfer case 4 is provided with a third transmission shaft arm 25, a third transmission shaft 26 is arranged in the third transmission shaft arm 25, the output end of the second transmission shaft 21 drives the third transmission shaft 26 to rotate through a gear of the third transfer case 4, the output end of the third transmission shaft 26 is provided with a rotor wing tilting device 5, the rotor wing tilting device 5 comprises a hub sleeve 30, a pair of blades 31 and four hub sleeve control hydraulic cylinders 32, the pair of blades 31 are symmetrically arranged at the top of the hub sleeve 30, one end of the hub sleeve 30 close to the top is connected with the third transmission shaft 26 through a universal coupling 35, one end of the universal coupling 35 is fixedly connected in the hub sleeve 30, the other end of the universal coupling is fixedly connected on the third transmission shaft 26, one end of the hub sleeve 30 close to the bottom is connected with the third transmission shaft arm 25 through the four hub sleeve control hydraulic cylinders 32, the four hub sleeve control hydraulic cylinders 32 are symmetrically arranged on the third transmission shaft, a piston rod of the hub sleeve control hydraulic cylinder 32 is provided with a spring buffer 36, one end of the spring buffer 36 is provided with a roller and is movably matched with the inner wall of the hub sleeve 30 through the roller, four auxiliary balance spring buffers 38 are symmetrically arranged on the third transmission shaft arm 25 above the hub sleeve control hydraulic cylinder 32 in a cross manner, one end of each auxiliary balance spring buffer 38 is provided with a roller and is movably matched with the inner wall of the hub sleeve 30 through the roller; second transfer case 3 and first transmission shaft arm 10 link up the department and are equipped with the transmission shaft and vert device 6, the transmission shaft verts device 6 and includes toothed disc 12 and toothed disc driving motor 13, second transfer case 3 passes through axle sleeve movable mounting on first transmission shaft arm 10, toothed disc 12 fixed mounting is on the axle sleeve of second transfer case 3, toothed disc driving motor 13's output is equipped with the drive gear who uses with the cooperation of toothed disc 12, toothed disc driving motor 13 fixed mounting is on first transmission shaft arm 10, and rotate as the axle center through gear drive second transfer case 3 with first transmission shaft arm 10.
The output shaft of the engine 1, the first transmission shaft 11, the second transmission shaft 21 and the third transmission shaft 26 are all transmitted through conical gears, four conical gears which are distributed in a cross shape are arranged in the first transfer case 2, two adjacent conical gears are meshed with each other, the four conical gears which are distributed in the cross shape correspond to the four first transmission shafts 11 respectively, two opposite first transmission shafts 11 are also provided with coaxial first transmission conical large gears, and the output shaft of the engine 1 is provided with a main transmission conical gear which is matched with the two first transmission conical large gears for use; three bevel gears are distributed in the second transfer case 3 in a T shape, the three bevel gears respectively correspond to the output end of the first transmission shaft 11 and the input ends of the two second transmission shafts 21, and the bevel gear at the output end of the first transmission shaft 11 drives the bevel gears at the input ends of the other two second transmission shafts 21 to rotate; two bevel gear transmissions are arranged in the third transfer case 4, wherein one bevel gear corresponds to the output end of the second transmission shaft 21, and the other bevel gear corresponds to the input end of the third transmission shaft 26.
Still be equipped with electromagnetism gag lever post 28 on the first transmission shaft arm 10, it has the spacing hole of using with electromagnetism gag lever post 28 cooperation to open on the gear disc 12 of transmission shaft tilting device 6.
The working mode and principle are as follows: the power take off end final drive conical gear of engine 1 drives two first transmission toper gear rotations, two first transmission toper gear fixed mounting are on two first transmission shafts 11 that correspond, four in the first transfer case 2 are the conical gear of cross distribution and drive four first transmission shafts 11 that correspond and rotate, two relative first transmission shafts 11 rotate opposite direction, every first transmission shaft 11 drives two second transmission shafts 21 again and rotates, two second transmission shaft 21 pivoted opposite direction, second transmission shaft 21 drives corresponding third transmission shaft 26 and rotates, paddle 31 on two third transmission shafts 26 of every group rotates opposite direction promptly, the rotational speed is synchronous, two rotor tilt devices 5 that every first transmission shaft arm 10 corresponds are a set of and keep synchro control. When the hub sleeve 30 rotates by taking the third transmission shaft arm 25 as an axis, the hub sleeve 30 is inclined towards the opposite direction by controlling the hydraulic cylinder 32 to extend through any one hub sleeve, so that the moment inclination angle of the rotation of the blade 31 is changed, and the flying attitude and direction are controlled; spring damper 36 and auxiliary counter spring damper 38 work in a movable fit with the inner wall of hub sleeve 30 to allow rotor tilter assembly 5 to rotate smoothly. The transmission shaft verts 3 whole second transfer cases that the device 6 control corresponds and uses first transmission shaft arm 10 as the rotatory swing of axle center, verts device 6 through two relative transmission shafts on every first transmission shaft arm 10 and does syntropy or reverse synchronous verts the control, enables the aircraft and does big power direction control, and the transmission shaft verts device 6 and rotor verts 5 synchronous cooperations of device and use, can make flight gesture and directional control flexible high efficiency more.
Claims (3)
1. A multi-shaft multi-directional tilting type multi-rotor aircraft transmission system is characterized by comprising an engine (1), a first transfer case (2), a second transfer case (3), a third transfer case (4), a rotor tilting device (5) and transmission shaft tilting devices (6), wherein four first transmission shaft arms (10) are symmetrically arranged on the first transfer case (2) in a cross manner, first transmission shafts (11) are respectively arranged in the four first transmission shaft arms (10), and an output shaft of the engine (1) drives the four first transmission shafts (11) to rotate through gears of the first transfer case (2); the output end of the first transmission shaft arm (10) is provided with a second transfer case (3), the second transfer case (3) is symmetrically provided with two second transmission shaft arms (20), second transmission shafts (21) are respectively arranged in the two second transmission shaft arms (20), and the output end of the first transmission shaft (11) drives the two second transmission shafts (21) to rotate through a gear of the second transfer case (3); the output end of the second transmission shaft arm (20) is provided with a third transfer case (4), the third transfer case (4) is provided with a third transmission shaft arm (25), a third transmission shaft (26) is arranged in the third transmission shaft arm (25), the output end of the second transmission shaft (21) drives the third transmission shaft (26) to rotate through a gear of the third transfer case (4), the output end of the third transmission shaft (26) is provided with a rotor tilting device (5), the rotor tilting device (5) comprises a hub sleeve (30), a pair of blades (31) and four hub sleeve control hydraulic cylinders (32), the pair of blades (31) are symmetrically arranged at the top of the hub sleeve (30), one end of the hub sleeve (30), which is close to the top, is connected with the third transmission shaft (26) through a universal coupling (35), one end of the universal coupling (35) is fixedly connected in the hub sleeve (30), and the other end of the universal coupling (35) is fixedly connected on the third transmission shaft (26), one end, close to the bottom, in the propeller hub sleeve (30) is connected with a third transmission shaft arm (25) through four propeller hub sleeve control hydraulic cylinders (32), the four propeller hub sleeve control hydraulic cylinders (32) are symmetrically installed on the third transmission shaft arm (25) in a cross manner, a piston rod of each propeller hub sleeve control hydraulic cylinder (32) is provided with a spring buffer (36), one end of each spring buffer (36) is provided with a roller and is movably matched with the inner wall of the propeller hub sleeve (30) through the roller, four auxiliary balance spring buffers (38) are symmetrically arranged on the third transmission shaft arm (25) above the propeller hub sleeve control hydraulic cylinders (32) in a cross manner, one end of each auxiliary balance spring buffer (38) is provided with a roller and is movably matched with the inner wall of the propeller hub sleeve (30) through the roller; second transfer case (3) and first transmission shaft arm (10) link up the department and are equipped with transmission shaft tilting device (6), transmission shaft tilting device (6) include toothed disc (12) and toothed disc driving motor (13), second transfer case (3) are through axle sleeve movable mounting on first transmission shaft arm (10), toothed disc (12) fixed mounting is on the axle sleeve of second transfer case (3), the output of toothed disc driving motor (13) is equipped with the drive gear who uses with toothed disc (12) cooperation, toothed disc driving motor (13) fixed mounting is on first transmission shaft arm (10), and rotate as the axle center through gear drive second transfer case (3) with first transmission shaft arm (10).
2. The transmission system of the multi-shaft multi-direction tilting multi-rotor aircraft as claimed in claim 1, wherein the output shaft of the engine (1), the first transmission shaft (11), the second transmission shaft (21) and the third transmission shaft (26) are all transmitted through bevel gears, four bevel gears distributed in a cross manner are arranged in the first transfer case (2), two adjacent bevel gears are meshed with each other, the four bevel gears distributed in the cross manner correspond to the four first transmission shafts (11) respectively, two opposite first transmission shafts (11) are also provided with coaxial first transmission bevel gear wheels, and the output shaft of the engine (1) is provided with a main transmission bevel gear matched with the two first transmission bevel gear wheels; three bevel gears are distributed in the second transmission box (3) in a T shape, the three bevel gears respectively correspond to the output end of the first transmission shaft (11) and the input ends of the two second transmission shafts (21), and the bevel gear at the output end of the first transmission shaft (11) drives the bevel gears at the input ends of the other two second transmission shafts (21) to rotate; two bevel gears are arranged in the third transfer case (4) for transmission, wherein one bevel gear corresponds to the output end of the second transmission shaft (21), and the other bevel gear corresponds to the input end of the third transmission shaft (26).
3. The multi-shaft multi-direction tilting multi-rotor aircraft transmission system according to claim 1, wherein the first transmission shaft arm (10) is further provided with an electromagnetic limit rod (28), and a limit hole matched with the electromagnetic limit rod (28) is formed in a gear disc (12) of the transmission shaft tilting device (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811539141.5A CN110615094A (en) | 2018-12-17 | 2018-12-17 | Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811539141.5A CN110615094A (en) | 2018-12-17 | 2018-12-17 | Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110615094A true CN110615094A (en) | 2019-12-27 |
Family
ID=68920837
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811539141.5A Pending CN110615094A (en) | 2018-12-17 | 2018-12-17 | Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110615094A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113060280A (en) * | 2021-05-13 | 2021-07-02 | 哈尔滨学院 | Multi freedom remote sensing unmanned aerial vehicle |
| CN115071960A (en) * | 2022-06-10 | 2022-09-20 | 四川大学 | Coaxial aircraft with variable propeller pitch |
| EP4269239A1 (en) * | 2022-04-25 | 2023-11-01 | Fundación Tecnalia Research & Innovation | Omnidirectional vehicle with passive revolute joints |
-
2018
- 2018-12-17 CN CN201811539141.5A patent/CN110615094A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113060280A (en) * | 2021-05-13 | 2021-07-02 | 哈尔滨学院 | Multi freedom remote sensing unmanned aerial vehicle |
| EP4269239A1 (en) * | 2022-04-25 | 2023-11-01 | Fundación Tecnalia Research & Innovation | Omnidirectional vehicle with passive revolute joints |
| WO2023208722A1 (en) * | 2022-04-25 | 2023-11-02 | Fundación Tecnalia Research & Innovation | Omnidirectional vehicle with passive revolute joints |
| CN115071960A (en) * | 2022-06-10 | 2022-09-20 | 四川大学 | Coaxial aircraft with variable propeller pitch |
| CN115071960B (en) * | 2022-06-10 | 2023-07-18 | 四川大学 | Coaxial aircraft with variable pitch |
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