CN214267982U

CN214267982U - Double-engine unmanned aerial vehicle

Info

Publication number: CN214267982U
Application number: CN202120169749.4U
Authority: CN
Inventors: 于进峰; 孟令恩; 张涛; 陈磊
Original assignee: Henan Kunyu Uav Technology Co ltd
Current assignee: Henan Kunyu Uav Technology Co ltd
Priority date: 2021-01-22
Filing date: 2021-01-22
Publication date: 2021-09-24
Anticipated expiration: 2031-01-22

Abstract

The utility model provides a two engine unmanned aerial vehicle, unmanned aerial vehicle is single rotor oil-driven unmanned aerial vehicle, including main rotor, main rotor connects on the oar presss from both sides, the oar presss from both sides through main shaft drive, the latter half of main shaft rotates and sets up in the gearbox, the first half of main shaft stretches out from the gearbox, be provided with two engine drive on the unmanned aerial vehicle on the fore-and-aft direction, the output shaft of every engine is to the clutch, fixedly connected with initiative synchronizing wheel on the output shaft of clutch, it is provided with driven synchronizing wheel to go out to rotate near the gearbox, through synchronous belt drive between initiative synchronizing wheel and the driven synchronizing wheel, be provided with input gear with the coaxial fixed of driven synchronizing wheel, fixedly connected with output gear on the main shaft, two input gear all mesh with output gear, two input gear are located output gear's front and back respectively, the fin passes through the engine drive at rear portion. This unmanned aerial vehicle sexual valence relative altitude.

Description

Double-engine unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned aerial vehicle, in particular to twin-engine unmanned aerial vehicle belongs to unmanned air vehicle technical field.

Background

The unmanned aerial vehicle can be widely applied to the scenes of agricultural plant protection, monitoring, high-altitude operation, point-to-point material conveying and the like; the existing unmanned aerial vehicles comprise an oil-driven unmanned aerial vehicle and an electric unmanned aerial vehicle, the electric unmanned aerial vehicle has simple mechanism, easy control and low cost, but has small integral takeoff weight and short endurance time, the oil-driven unmanned aerial vehicle has more complex structure, but can realize longer endurance time, so the electric unmanned aerial vehicle has advantages under the application scenes of small load and short endurance time, and needs to be realized by the oil-driven unmanned aerial vehicle under the application requirement of large load and long endurance time, in the oil-driven unmanned aerial vehicle, a single rotor only has a rotor wing but does not have a fixed wing, so a large takeoff field and land space is saved, the transportation and application operation scenes of the oil-driven unmanned aerial vehicle can be very flexible, but the large-displacement engine required by the unmanned aerial vehicle with large takeoff weight basically realizes the localization in the small-displacement engine in China at present, and can also meet the requirement when being applied to the unmanned aerial vehicle, however, engines with large displacement (such as more than 250 CC) are mainly imported, the price of the imported engines is doubled or even higher than that of domestic engines, even if the prices of many foreign engines which can be used for unmanned aerial vehicles are forbidden to sell in China, and even if the foreign engines achieve large takeoff weight, the weight of the engines is large, and the maximum load of the engines is limited under the condition that the whole takeoff weight is certain. Above-mentioned various factors have all tied the development of the oil driven unmanned aerial vehicle of big weight of taking off, and how can enough realize that big weight of taking off can also realize that low input cost is the technical problem that needs to solve in the oil driven unmanned aerial vehicle development of big weight of taking off.

Disclosure of Invention

An object of the utility model is to overcome the above-mentioned problem that exists on the present oil moves unmanned aerial vehicle, provide a twin-engine unmanned aerial vehicle.

In order to realize the purpose of the utility model, the following technical proposal is adopted: a double-engine unmanned aerial vehicle is a single-rotor oil-driven unmanned aerial vehicle and comprises a main rotor, wherein the main rotor is connected to a paddle clamp, the paddle clamp is driven by a main shaft, the lower half part of the main shaft is rotatably arranged in a gearbox, the upper half part of the main shaft extends out of the gearbox, two engines are arranged on the unmanned aerial vehicle in the front-back direction for driving, and the two engines drive the main shaft in the same direction; the output shaft of each engine is connected to the clutch, a driving synchronizing wheel is fixedly connected to the output shaft of the clutch, a driven synchronizing wheel is arranged in a mode of rotating close to the gearbox, the driving synchronizing wheel and the driven synchronizing wheel are in synchronous belt transmission, an input gear is coaxially and fixedly arranged with the driven synchronizing wheel, an output gear is fixedly connected to the main shaft, the two input gears are all meshed with the output gear, the two input gears are respectively positioned in the front of and behind the output gear, and the tail fin is driven by the engine at the rear portion.

Further, the method comprises the following steps of; the tail wing speed-changing driving belt wheel is coaxially arranged with the driving synchronous wheel at the rear part, and a belt for driving the tail wing is wound on the driving belt wheel and is twisted for 90 degrees and then is wound on a driven belt wheel which is coaxial with the tail wing.

Further, the method comprises the following steps of; the driving synchronous wheel of the clutch output shaft connected with the engine at the rear part is a two-grooved wheel, one groove is in transmission with the driven synchronous wheel through the synchronous belt, and the belt in the other groove is in transmission with the driven belt wheel of the tail wing after being twisted for 90 degrees.

The utility model discloses an actively beneficial technological effect lies in: this unmanned aerial vehicle adopts the power of two sets of generators drives a main shaft simultaneously around, it can realize great weight of taking off to have realized adopting two small discharge capacity generators on single rotor unmanned aerial vehicle, through experimental, the biggest weight of taking off of two small discharge capacity generators is with the big engine weight of taking off of discharge capacity that adds of two small discharge capacity generators, because big engine's main shaft weight is general very heavy, so the unmanned aerial vehicle of this application is under the condition of the weight of taking off the same biggest, its self weight is less than the unmanned aerial vehicle of making with the big engine of discharge capacity even, this can also improve unmanned aerial vehicle's load, arrange around two engines, can reduce unmanned aerial vehicle's width, thereby reduce flight resistance. The utility model discloses a drive belt wheel is connected on the drive shaft that traditional fin drive adopted to export from the gearbox, adopts two engines after, if still draw forth the drive power of fin in the gearbox, the structure will become very complicated, and space installation is last also very inconvenient, the utility model discloses in with the drive belt wheel of fin and the coaxial drive that has realized the fin of the initiative synchronizing wheel on the engine at rear portion.

Drawings

Fig. 1 is a schematic diagram of the present invention using two sheaves.

Figure 2 is a discrete schematic view of the rear portion of the tail variable speed drive pulley of the present invention.

Detailed Description

In order to explain the utility model more fully, the utility model provides an implementation example. These examples are merely illustrative of the present invention and do not limit the scope of the present invention.

The invention is explained in further detail with reference to the drawings, in which the reference symbols are: 1: a main shaft; 2: a gearbox; 3: a paddle clamp; 4: an engine A; 5: a clutch A; 6: a driving synchronizing wheel A; 7: a synchronous belt A; 8: a driven synchronizing wheel A; 9: an input gear A; 10: an output gear; 11: an engine B; 12: a clutch B; 13: a driving synchronizing wheel B; 14: a synchronous belt B; 15: a driven synchronizing wheel B; 16: an input gear B; 17: a tail wing; 18: a tail pipe; 19: a drive pulley.

As shown in the attached drawings, the unmanned aerial vehicle is a single-rotor oil-driven unmanned aerial vehicle and comprises a main rotor, wherein the main rotor is connected to a paddle clamp 3, the paddle clamp is driven by a main shaft 1, the lower half part of the main shaft is rotationally arranged in a gearbox 2, the upper half part of the main shaft extends out of the gearbox, two engines are arranged on the unmanned aerial vehicle in the front-back direction for driving, and the two engines drive the main shaft in the same direction; the two engines are as shown in an engine a4 and an engine B11 in the figure, the structures of the driving main shafts of the two generators are the same, hereinafter, taking the engine a at the rear as an example, the output shaft of the engine a is connected to a clutch a5, a driving synchronizing wheel a6 is fixedly connected to the output shaft of the clutch a5, a driven synchronizing wheel A8 is rotatably arranged close to the output of the gearbox, the driving synchronizing wheel a and the driven synchronizing wheel a are transmitted through a synchronizing belt a7, an input gear a9 is coaxially and fixedly arranged with the driven synchronizing wheel, an output gear 10 is fixedly connected to the main shaft, the two input gears a and B16 are both meshed with the output gear 10, the two input gears are respectively positioned in front and rear of the output gear, and the tail fin 16 is driven through the engine a4 at the rear.

The specific mechanism of the tail fin can be: a tail variable-speed driving belt wheel 19 is coaxially arranged with the driving synchronous wheel at the rear part, and a belt for driving the tail is wound on the driving belt wheel and twisted for 90 degrees and then wound on a driven belt wheel coaxial with the tail. This kind of mode is shown in fig. 2, and current unmanned aerial vehicle's fin drive adopts the belt to twist reverse 90 degrees back and drive through an output wheel on the gearbox basically, the utility model discloses in change into and adopt the rear portion engine to drive.

The specific mechanism of the tail wing can also be as follows: the driving synchronous wheel of the clutch output shaft connected with the engine at the rear part is two grooved wheels, in the figure 1, the synchronous driving wheel A is two grooved wheels, one groove is in transmission with the driven synchronous wheel through the synchronous belt, and the belt in the other groove is in transmission with the driven belt wheel of the tail wing after being twisted for 90 degrees. Belt twist 90 degree drive is prior art and is not shown in either figure.

The innovation in this application lies in having adopted two engines drive a main shaft of arranging around, having adopted the rear portion engine to pass through belt drive simultaneously and has solved fin driven problem, and other parts all can adopt the prior art on the present single rotor unmanned aerial vehicle.

The effect of the utility model is illustrated by taking a domestic two-stroke 170CC oil-driven unmanned aerial vehicle as an example, a single 170CC engine weighs about 3.8kg, the maximum takeoff weight of the oil-driven unmanned aerial vehicle driven by the single 170CC engine is about 50kg, and the effective load is about 17 kg; the ratio of the unmanned aerial vehicle's own weight to payload is about 2: 1. According to the utility model provides a scheme adopts two generators of 170cc discharge capacity, and unmanned aerial vehicle's the biggest weight of taking off is about 150kg, and is equivalent with the import with the biggest weight basis of taking off of engine drive's unmanned aerial vehicle of discharge capacity, and the utility model discloses a payload is about 60kg, and the ratio of unmanned aerial vehicle self weight and payload is about 1.5: 1. The weight of two 170cc engines is about 7.6kg, the weight of a single engine with the discharge capacity of about 350cc imported from abroad is about 14kg, and the weight of the unmanned aerial vehicle can be reduced by 6-7kg only from the engine. So the technical scheme of the utility model the oil that can effectual promotion take-off weight greatly moves unmanned aerial vehicle development.

After the embodiments of the present invention have been described in detail, those skilled in the art can clearly understand that various changes and modifications can be made without departing from the scope and spirit of the above claims, and any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention all fall within the scope of the technical solution of the present invention, and the present invention is not limited to the embodiments of the examples given in the specification.

Claims

1. The utility model provides a two engine unmanned aerial vehicle, unmanned aerial vehicle is single rotor oil moves unmanned aerial vehicle, including main rotor, main rotor connects on the oar presss from both sides, and the oar presss from both sides through spindle drive, and the latter half of main shaft rotates and sets up in the gearbox, and the first half of main shaft stretches out its characterized in that from the gearbox: two engines are arranged on the unmanned aerial vehicle in the front-back direction for driving, and the two engines drive the main shaft in the same direction; the output shaft of each engine is connected to the clutch, a driving synchronizing wheel is fixedly connected to the output shaft of the clutch, a driven synchronizing wheel is arranged in a mode of rotating close to the gearbox, the driving synchronizing wheel and the driven synchronizing wheel are in synchronous belt transmission, an input gear is coaxially and fixedly arranged with the driven synchronizing wheel, an output gear is fixedly connected to the main shaft, the two input gears are all meshed with the output gear, the two input gears are respectively positioned in the front of and behind the output gear, and the tail fin is driven by the engine at the rear portion.

2. A twin-engine drone according to claim 1, characterised in that: the tail wing speed-changing driving belt wheel is coaxially arranged with the driving synchronous wheel at the rear part, and a belt for driving the tail wing is wound on the driving belt wheel and is twisted for 90 degrees and then is wound on a driven belt wheel which is coaxial with the tail wing.

3. A twin-engine drone according to claim 1, characterised in that: the driving synchronous wheel of the clutch output shaft connected with the engine at the rear part is a two-grooved wheel, one groove is in transmission with the driven synchronous wheel through the synchronous belt, and the belt in the other groove is in transmission with the driven belt wheel of the tail wing after being twisted for 90 degrees.