CN218463883U - Multi-rotor-wing type unmanned aerial vehicle transmission mechanism - Google Patents

Abstract

The application discloses many rotor formula unmanned aerial vehicle drive mechanism, the engine passes through one way clutch and links to each other with input gear, input gear meshes with four diverging gear mutually, diverging gear links to each other with power transmission shaft through the diaphragm coupling respectively, power transmission shaft passes through the diaphragm coupling and links to each other with branch's reduction gears, branch's reduction gears includes bevel gear reduction gear and planetary gear reduction gear, power transmission shaft connects in the bevel gear reduction gear, the bevel gear reduction gear is connected in planetary gear reduction gear, planetary gear reduction gear connects in the rotor. The transmission mechanism can realize high-power transmission, has high reliability, and realizes maneuvering flight by changing the total distance of each branch rotor wing; compared with a motor direct-drive multi-rotor aircraft, the multi-rotor aircraft has higher efficiency and smaller control difficulty, can realize higher-load flight, and meets the application of more scenes; compared with a helicopter with a single rotor wing with a tail reducer in the same magnitude, the helicopter has smaller size and storage space, and is suitable for being used as a carrier-based aircraft.

Description

Multi-rotor-wing type unmanned aerial vehicle transmission mechanism

Technical Field

The utility model belongs to the technical field of transmission system structural design, especially, relate to a many rotor formula unmanned aerial vehicle drive mechanism.

Background

The multi-rotor aircraft is widely applied to reconnaissance, patrol, information acquisition, command and scheduling, efficient search and rescue, emergency rescue and disaster relief and the like due to simple structure, flexible operation and good maneuvering performance. But present many rotors mostly all are motor direct drive rotor, control the gesture of aircraft through changing the motor speed, because battery energy density is low for electricelectric's many rotors unmanned aerial vehicle inefficiency and machine carry weight little, the mileage of continuing a journey is short, restricts many rotors toward more application and development of direction greatly.

At present, most domestic multi-rotor wings have the take-off weight of about 5 kg-200 kg, the larger take-off weight is basically blank at home, pure electric drive is not practical when the multi-rotor wings above 200kg use pure electric drive, and each motor needs larger volume and weight, so if a 100kw engine is adopted, the maximum take-off weight of 530kg can be finally realized, 100kg of fuel oil can be added except the self equipment weight, the endurance lasts for 5-6 h, the practical limit of increase is 3000 m, and the application scenes with the performance capable of being satisfied are greatly increased, such as material transportation throwing, electric power line patrol, geographical surveying and mapping, and integration and the like. And the multi-rotor wing is simple to operate, occupies a small space compared with a same-magnitude single-rotor wing helicopter with a tail rotor, is suitable for being used as a carrier-based aircraft, and meets the requirements of naval equipment.

Therefore the utility model discloses a transmission of many rotors of a section, this transmission is through an engine power input, carry out four reposition of redundant personnel with the power of engine, through power transmission shaft and diaphragm coupling with power transmission to each branch rotor, through one-level bevel gear switching-over speed reduction and one-level planetary gear speed reduction, final output is to the rotor end, this transmission can keep the rotational speed of four rotors the same, total distance through changing different rotors realizes motor flight, this transmission has efficiently, transmission power is high, advantage such as the reduction ratio is big, because the engine can be when making the aircraft have big loading capacity and long voyage as the power input source, the drawback and the shortcoming of electronic many rotors have been remedied.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a transmission of many rotor formula unmanned aerial vehicle through providing, the electricelectric's that provides among the solution background art many rotor unmanned aerial vehicle inefficiency and machine carries weight little, the short scheduling problem of continuation of the journey mileage. The transmission mechanism has the advantages of high transmission power, large reduction ratio, high transmission efficiency and the like. The rotating speeds of the two rotors are consistent, the two rotors rotate forwards, the two rotors rotate backwards, the method can be used for offsetting the reactive torque, and the maneuvering flight of the aircraft is realized by changing the total distance of the rotors.

In order to realize the purpose of the utility model, the utility model discloses a multi-rotor unmanned aerial vehicle transmission mechanism, which comprises an engine, a one-way clutch, an input gear, a shunt gear, a diaphragm coupling, a power transmission shaft and a branch speed reducing mechanism; the engine is connected with the input gear through a one-way clutch, and the one-way clutch is used for preventing the rotor wing from reversely carrying the engine; the input gear is meshed with the four shunting gears, the shunting gears are in a uniform distribution state, the shaft included angle is 90 degrees, and the included angle between every two of the four shunting gears is 90 degrees; the split gear is respectively connected with the power transmission shaft through the diaphragm coupling to realize branch power transmission, and the diaphragm coupling is used for compensating axial and angle deviations; the power transmission shaft is connected with a branch speed reducing mechanism through a diaphragm coupling, the branch speed reducing mechanism comprises a bevel gear speed reducer and a planetary gear speed reducer, the power transmission shaft is connected with the bevel gear speed reducer, the bevel gear speed reducer is connected with the planetary gear speed reducer, and the planetary gear speed reducer is connected with the rotor;

the power and the rotating speed of the engine are transmitted to the input gear through the one-way clutch, and the input gear is meshed with the four shunt gears simultaneously, so that the power and the rotating speed are reversed and shunted; the four shunt gears are connected with one end of the power transmission shaft through the diaphragm coupling, so that the remote transmission of power and rotating speed is realized; the other end of the power transmission shaft is connected with the bevel gear speed reducer of each branch through a diaphragm coupling, and the bevel gear speed reducer realizes power reversing and speed reduction again; the bevel gear reduction gear links to each other with planetary gear reduction gear, and power and rotational speed realize the moment of torsion that the big reduction ratio increased the planet carrier simultaneously through planetary gear reduction gear, and finally the planet carrier passes through the propeller hub and transmits engine speed and moment of torsion to the rotor blade, controls unmanned aerial vehicle flight attitude through changing each paddle collective pitch.

Furthermore, the bevel gear reducer comprises a branch input gear and a reversing reduction gear, the branch input gear and the reversing reduction gear are bevel gears, the intersection angle of the installation shafts is 90 degrees, the reversing reduction gear is connected to the planetary gear reducer, and the planetary gear reducer is connected to the rotor.

Furthermore, the planetary gear reducer comprises a fixed gear ring, four planet wheels, a sun wheel and a planet carrier; the fixed gear ring, the four planet wheels, the sun wheel and the planet carrier are coaxially arranged; the four planet wheels and the sun wheel are arranged in the fixed gear ring, the sun wheel is positioned in the middle, and the four planet wheels are uniformly distributed around the sun wheel; the two liang contained angles of planet wheel are 90, and four planet wheels link to each other with the planet carrier respectively, and four planet wheels divide the power reposition of redundant personnel of sun gear then converge power through the planet carrier and export.

Further, the one-way clutch is a wedge type clutch.

Furthermore, the input gear and the four shunt gears are bevel gears made of 18Cr2Ni4WA, the input gear and the shunt gears are in speed-increasing transmission, and the speed-increasing ratio is 2-3.

Furthermore, the compensation capacity of the diaphragm coupling is axial offset compensation of 0-3 mm, and the angular offset compensation of 0-3 degrees.

Furthermore, the power transmission shaft is made of aviation secondary aluminum or aviation seventh aluminum, the outer diameter of the shaft is 35 mm-45 mm, and the wall thickness is 1 mm-1.5 mm.

Furthermore, 18Cr2Ni4WA is adopted as the materials of the branch input gear and the reversing reduction gear, and the heat treatment is carburizing and quenching.

Furthermore, the fixed gear ring, the planet gear and the sun gear are made of 32Cr3Mo1V, the heat treatment is surface nitriding treatment, and the planet carrier is made of TC4 titanium alloy; the four planet wheels are installed in an evenly distributed state, and the uniform load transmission of power is realized.

Furthermore, the installation directions of the reversing reduction gears of the two branches on the same diagonal are the same, and the installation directions of the reversing reduction gears on different diagonals are opposite, so that the rotating speeds of the rotors are opposite, the reaction torque is balanced, and the aircraft is kept stable.

Compared with the prior art, the utility model discloses a show the progress and lie in: 1) The transmission mechanism can realize high-power transmission, has high reliability, realizes maneuvering flight by changing the total distance of each branch rotor wing, and has higher efficiency and smaller control difficulty compared with a motor direct-drive multi-rotor-wing aircraft; 2) Because the transmission mechanism is driven by the engine, when the 100kW engine is used as power input, the maximum takeoff weight of the whole aircraft can reach 530 kg-550 kg, and 100kg of fuel can be carried, so that larger-load flight can be realized, the endurance mileage can also reach 5 h-6 h, the defects of electric multiple rotors are overcome, and more scenes of application can be realized; 3) Compared with a helicopter with a single rotor and a tail reducer in the same magnitude, the multi-rotor type helicopter has smaller size and storage space, is suitable for being used as a carrier-based aircraft, meets the requirements of naval equipment, and fills up the blank at home and abroad for the airplane in the takeoff weight interval.

To more clearly illustrate the functional characteristics and structural parameters of the present invention, the following description is further provided with reference to the accompanying drawings and the detailed description.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:

fig. 1 is an overall schematic view of a multi-rotor type unmanned aerial vehicle transmission mechanism;

FIG. 2 is a schematic diagram of a power split transmission;

fig. 3 is a schematic view of the branch reduction mechanism 1;

fig. 4 is a schematic view of the branch reduction mechanism 2;

FIG. 5 is a schematic illustration of a planetary gear reducer configuration;

FIG. 6 is a schematic view of a planet carrier structure;

the reference numbers in the figures are: 1. the engine, 2, one-way clutch, 3, input gear, 4, reposition of redundant personnel gear, 5, diaphragm coupling, 6, power transmission shaft, 7, branch input gear, 8, switching-over reduction gear, 9, decide the ring gear, 10, planet wheel, 11, sun gear, 12, planet carrier.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments; based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

As shown in fig. 1, a multi-rotor unmanned aerial vehicle transmission mechanism comprises an engine 1, a one-way clutch 2, an input gear 3, a shunt gear 4, a diaphragm coupling 5, a power transmission shaft 6, a branch input gear 7, a reversing reduction gear 8, a fixed gear ring 9, a planet gear 10, a sun gear 11 and a planet carrier 12. The engine 1 is connected with an input gear 3 through a one-way clutch 2, the purpose is to prevent the rotor from reversely taking the engine 1, the input gear 3 is meshed with four shunt gears 4, the mechanism can shunt power into four branches, the shunt gears 4 are connected with a power transmission shaft 6 through a diaphragm coupling 5, the diaphragm coupling 5 is used for compensating axial and circumferential deviation and displacement, and the power transmission shaft 6 is connected with a branch input gear 7 through the diaphragm coupling 5 to realize branch power input. The branch input gear 7 and the reversing reduction gear 8 realize one-stage speed reduction and power reversing. Reversing reduction gears 8 are connected with a planetary gear reducer to realize secondary speed reduction, the planetary gear reducer comprises a fixed gear ring 9, a planetary gear 10, a sun gear 11 and a planetary carrier 12, the planetary carrier 12 transmits power and rotating speed to respective rotors, two reversing reduction gears 8 are opposite to the other two installation directions, the rotors are finally determined to turn differently, the counter torque can be offset at the moment, and the stability of the airplane is kept.

As shown in fig. 2, the input gear 3 is meshed with four shunt gears 4, the shunt gears 4 are in an evenly distributed state, the included angle of a shaft is 90 degrees, the included angle between every two of the four shunt gears 4 is 90 degrees, the input gear 3 and the four shunt gears 4 are bevel gears, the material is 18Cr2Ni4WA, the material is high-quality low-carbon steel, the surface hardness of the gears is improved by carburizing and quenching, the power shunting and reversing are realized, the transmission load is large, the transmission efficiency reaches over 97 percent, the position is in speed-increasing transmission, and the speed-increasing ratio is 2-3.

As shown in fig. 3 and 4, the four branch speed reducing mechanisms are identical in pairs, each speed reducing mechanism comprises a first-stage bevel gear speed reducer for speed reduction and reversing and a second-stage planetary gear speed reducer, each bevel gear speed reducer comprises a branch input gear 7 and a reversing speed reducing gear 8, both bevel gears are arranged, the intersection angle of the installation shafts is 90 degrees, the gear material adopts 18Cr2Ni4WA, and the heat treatment is carburizing and quenching. The planetary reduction mechanism comprises a fixed gear ring 9, four planet wheels 10, a sun wheel 11 and a planet carrier 12. The materials of the sun gear 11, the planet gear 10 and the fixed gear ring 9 are 32Cr3Mo1V, and the heat treatment adopts surface nitriding treatment; the material of the planet carrier 12 adopts TC4, so that the strength is high, the weight is small, and the power-weight ratio of the airplane is greatly improved. The four planet wheels 10 are installed in an evenly distributed state, and the uniform load transmission of power is realized. The speed reducing mechanism can realize a large speed reducing ratio which is 8-10. The installation directions of the reversing reduction gears 8 of the two branches on the same diagonal are the same, and the installation directions of the reversing reduction gears 8 on different diagonals are opposite, so that the purposes of realizing the opposite rotating speeds of the rotors and balancing the reaction torque are achieved, and the aircraft is kept stable. This drive mechanism can keep four rotor rotational speeds unanimous, realizes maneuver flight through the collective pitch that changes every branch rotor, reduces the aircraft flight control degree of difficulty.

As shown in fig. 5 and 6, the fixed gear ring 9, the four planet gears 10, the sun gear 11 and the planet carrier 12 are coaxially arranged; the four planet wheels 10 and the sun wheel 11 are arranged inside the fixed gear ring 9, the sun wheel 11 is arranged in the middle, and the four planet wheels 10 are uniformly distributed around the sun wheel 11; the included angle of each two planet gears 10 is 90 degrees, the four planet gears 10 are respectively connected with the planet carrier 12, and the four planet gears 10 divide the power of the sun gear 11 and then converge and output the power through the planet carrier 12.

Specifically, in the present embodiment, the one-way clutch 2 employs a sprag type clutch. The compensation capacity of the diaphragm coupling 5 is axial offset compensation of 0-3 mm, and angular offset compensation of 0-3 degrees.

Specifically, in the embodiment, the power transmission shaft 6 is made of aviation secondary aluminum or aviation seventh aluminum, the outer diameter of the shaft is 35 mm-45 mm, and the wall thickness is 1 mm-1.5 mm. The transmission efficiency of the power transmission shaft 6 can reach more than 95%, the tail end of the power transmission shaft 6 is connected with the branch reduction gear 7, the reversing reduction gear 8 is connected with the planetary gear reducer, the large reduction ratio is realized, the output torque of the planet carrier 12 is increased at the same time, the power of the engine is finally transmitted to the rotor wing, and the transmission power of the whole transmission system reaches more than 90%.

The working principle and the flow of the device are as follows: the power and the rotating speed of the engine 1 are transmitted to the input gear 3 through the one-way clutch 2, and the input gear 3 is meshed with the four shunt gears 4 simultaneously, so that the reversing and the shunting of the power and the rotating speed are realized; the four shunt gears 4 are connected with one end of a power transmission shaft 6 through a diaphragm coupling 5, so that the remote transmission of power and rotating speed is realized; the other end of the power transmission shaft 6 is connected with the bevel gear speed reducer of each branch through a diaphragm coupling 5, and the bevel gear speed reducer realizes power reversing and speed reduction again; the bevel gear reducer is connected with the planetary gear reducer, the power and the rotating speed are reduced greatly through the planetary gear reducer, meanwhile, the torque of the planet carrier 12 is increased, finally, the planet carrier 12 transmits the rotating speed and the torque of the engine 1 to the rotor blades through the propeller hub, and the flying attitude of the unmanned aerial vehicle is controlled by changing the total distance of the blades.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (10)

1. A multi-rotor unmanned aerial vehicle transmission mechanism is characterized by comprising an engine (1), a one-way clutch (2), an input gear (3), a shunt gear (4), a diaphragm coupling (5), a power transmission shaft (6) and a branch speed reduction mechanism; the engine (1) is connected with the input gear (3) through a one-way clutch (2), and the one-way clutch (2) is used for preventing the rotor wing from reversely carrying the engine (1); the input gear (3) is meshed with the four shunt gears (4), the shunt gears (4) are in a uniformly distributed state, the included angle of the shafts is 90 degrees, and the included angle between every two of the four shunt gears (4) is 90 degrees; the shunt gear (4) is connected with the power transmission shaft (6) through the diaphragm coupling (5) respectively to realize branch power transmission, and the diaphragm coupling (5) is used for compensating axial and angle deviations; the power transmission shaft (6) is connected with a branch speed reducing mechanism through a diaphragm coupling (5), the branch speed reducing mechanism comprises a bevel gear speed reducer and a planetary gear speed reducer, the power transmission shaft (6) is connected with the bevel gear speed reducer, the bevel gear speed reducer is connected with the planetary gear speed reducer, and the planetary gear speed reducer is connected with the rotor.

2. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 1, wherein the bevel gear reducer comprises a branch input gear (7) and a reversing reduction gear (8), the branch input gear (7) and the reversing reduction gear (8) are both bevel gears, the intersection angle of the installation shafts is 90 °, the reversing reduction gear (8) is connected to a planetary gear reducer, and the planetary gear reducer is connected to the rotor.

3. A multi-rotor unmanned aerial vehicle transmission according to claim 1, wherein the planetary gear reducer comprises a fixed ring gear (9), four planet gears (10), a sun gear (11) and a planet carrier (12); the fixed gear ring (9), the four planet wheels (10), the sun wheel (11) and the planet carrier (12) are coaxially arranged; the four planet wheels (10) and the sun wheel (11) are arranged inside the fixed gear ring (9), the sun wheel (11) is arranged in the middle, and the four planet wheels (10) are uniformly distributed around the sun wheel (11); the included angle of each two planet gears (10) is 90 degrees, the four planet gears (10) are respectively connected with the planet carrier (12), and the four planet gears (10) are used for dividing the power of the sun gear (11) and then converging the power through the planet carrier (12) for output.

4. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 1, wherein the one-way clutch (2) is a wedge clutch.

5. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 1, wherein the input gear (3) and the four splitter gears (4) are bevel gears and made of 18Cr2Ni4WA, and the input gear (3) and the splitter gears (4) are in step-up transmission with a step-up ratio of 2-3.

6. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 1, wherein the compensation capability of the diaphragm coupling (5) is axial offset compensation of 0-3 mm and angular offset compensation of 0-3 °.

7. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 1, wherein the power transmission shaft (6) is made of aviation secondary aluminum or aviation seven-series aluminum, the outer diameter of the shaft is 35 mm-45 mm, and the wall thickness is 1 mm-1.5 mm.

8. A multi-rotor unmanned aerial vehicle drive mechanism as claimed in claim 2, wherein the branch input gear (7) and the reversing reduction gear (8) are made of 18Cr2Ni4WA, and the heat treatment is carburizing and quenching.

9. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 3, wherein the fixed gear ring (9), the planetary gear (10) and the sun gear (11) are made of 32Cr3Mo1V, the heat treatment is surface nitriding, and the planet carrier (12) is made of TC4.

10. The transmission mechanism of multi-rotor unmanned aerial vehicle according to claim 2, wherein the direction of installation of the reversing reduction gears (8) of the two branches on the same diagonal is the same, and the direction of installation of the reversing reduction gears (8) on different diagonals is opposite.

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