CN210102007U - Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing - Google Patents
Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing Download PDFInfo
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- CN210102007U CN210102007U CN201920832578.1U CN201920832578U CN210102007U CN 210102007 U CN210102007 U CN 210102007U CN 201920832578 U CN201920832578 U CN 201920832578U CN 210102007 U CN210102007 U CN 210102007U
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Abstract
The utility model provides an oil moves flight and electronic rotary wing VTOL unmanned aerial vehicle that combines together that takes off and land, it includes oil moves engine (1), characterized by oil move engine (1) with the driving shaft of driving and driven band pulley and belt means (3) link to each other, the driven shaft one end of driving and driven band pulley and belt means (3) links to each other with the drive shaft of preceding flight paddle (4) through first clutch (7), the other end passes through second clutch (10) and links to each other with generator (11), generator (11) and motor (21) electrical connection, the output shaft of motor (21) is direct or link to each other with the drive shaft of taking off and land rotor blade (22) through a reduction gears. The utility model discloses can reduce a quick-witted complete machine weight by a wide margin, improve flight performance.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle technique and specifically relates to an unmanned helicopter of rotor formula of VTOL, specifically speaking are oil-powered flight and electronic rotary wing VTOL unmanned aerial vehicle who combines together that takes off and land.
Background
At present, for a vertical take-off and landing aircraft with rotary wings, an oil-driven engine is generally adopted, a take-off and landing rotor system and a front flying propeller are driven according to needs by means of a clutch, the transmission scheme needs too many connecting mechanisms and transmission mechanisms, the take-off and landing rotor system and the front flying system are far away from each other, the number of parts is large, the maintenance is relatively complex, and the overall weight of the transmission system is relatively large.
In recent years, in order to increase lifting power and reduce the total power consumption of an oil engine, people adopt an electric auxiliary lifting technical scheme, a battery is used for providing power in a take-off stage, and the oil engine is used for driving an airplane to fly in a flat flying stage, so that the power of the oil engine can be greatly reduced, and the manufacturing and operating cost of the engine is reduced. But the biggest shortcoming that this kind of technical scheme brought is the unmanned aerial vehicle self weight's increase by a wide margin, and on the other hand increases the consumption again, reduces the load capacity.
Therefore, when improving unmanned aerial vehicle performance and power, reduce unmanned aerial vehicle self weight and also be the important index that unmanned aerial vehicle designed, be the important measure that improves unmanned aerial vehicle performance.
SUMMERY OF THE UTILITY MODEL
The utility model aims at designing a rotary wing VTOL unmanned aerial vehicle that oil moves flight and electronic take-off and land combined together to current unmanned aerial vehicle convey flight paddle and take off and land rotor paddle department with power because of the mechanical transmission system that needs complicacy and lead to complete machine weight to influence the problem of flight performance greatly.
The technical scheme of the utility model is that:
the utility model provides an oil moves flight and electronic rotary wing VTOL unmanned aerial vehicle who combines together that takes off and land, it includes oil engine 1, characterized by oil engine 1 with the driving shaft of driving band pulley and belt set 3 links to each other, driving shaft one end of driving band pulley and belt set 3 links to each other with the drive shaft of preceding flight paddle 4 through first clutch 7, the other end passes through second clutch 10 and links to each other with generator 11, generator 11 and motor 21 electrical connection, the output shaft of motor 21 directly or links to each other with the drive shaft of taking off and land rotor blade 22 through a reduction gears.
One end of the driven shaft connected with the generator is connected with a speed increaser, and an output shaft of the speed increaser is connected with an input shaft of the generator.
The speed reducing mechanism comprises a coupler 20, a driving bevel gear 23, a driven bevel gear 24, a straight-tooth pinion gear 15 and a straight-tooth gearwheel 14, an output shaft of a motor 21 is connected with the driving bevel gear 23 through the coupler 20, the driven bevel gear 24 is meshed with the driving bevel gear 23, a central shaft of the driven bevel gear 24 is coaxial with a central shaft of the straight-tooth pinion gear 15, the straight-tooth gearwheel 14 is meshed with the straight-tooth pinion gear 15, and a driving shaft of a lifting rotor blade 22 is coaxial with the central shaft of the straight-tooth gearwheel 14.
The output shaft of the motor is provided with a coaxial bevel gear, and the driving shaft of the lifting rotor blade 22 is provided with a bevel gear matched with the coaxial bevel gear.
The generator is also connected with an electric storage battery through a bidirectional inverter, and the electric storage battery supplies power for the motor or the airborne electric equipment.
The utility model has the advantages that:
the utility model divides the take-off and landing rotor system and the front flying propeller system into two independent parts, the front flying system adopts the oil-driven engine to directly drive through the clutch, and the engine is connected with a generator through the clutch; the lifting system is driven by a motor, and the electric quantity required by the motor during working is provided after the oil-driven engine 1 drives a generator to generate electricity. The two systems are mutually independent, a large number of mechanical connection parts are omitted, and meanwhile, the motors of the take-off and landing rotor systems do not need to be powered by storage batteries and only need to be directly powered by the power lines connected with the generator 11 driven by the oil-driven engine 1, so that the weight of the power transmission system of the airplane can be greatly reduced, and the power transmission system is very favorable for the aircraft.
The utility model discloses the method is simple, and maneuverability is strong.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is an electrical schematic diagram of the present invention.
In the figure: 1-oil-driven engine, 2-deep groove ball bearing, 3-main driven pulley and belt, 4-front flying paddle, 5-deep groove ball bearing, 6-deep groove ball bearing, 7-first clutch, 8-deep groove ball bearing, 9-deep groove ball bearing, 10-second clutch, 11-generator, 12-tapered roller bearing, 13-deep groove ball bearing, 14-straight-tooth big gear, 15-straight-tooth small gear, 16-deep groove ball bearing, 17-deep groove ball bearing, 18-tapered roller bearing, 19-tapered roller bearing, 20-coupler, 21-motor, 22-lifting rotor paddle, 23-driving bevel gear, 24-driven bevel gear, 25-tapered roller bearing, 26-tapered roller bearing, 27-tapered roller bearing, 28 deep groove ball bearing.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and examples.
The first embodiment.
As shown in fig. 1 and 2.
The utility model provides an oil moves rotatory wing VTOL unmanned aerial vehicle that flight and electronic take-off and landing combined together, it includes oil-driven engine 1, oil-driven engine 1 link to each other with the driving shaft of driving and driven band pulley and belt means 3, driving shaft one end of driving and driven band pulley and belt means 3 links to each other with the drive shaft of preceding flight paddle 4 through first clutch 7, the other end passes through second clutch 10 and links to each other with generator 11, generator 11 and motor 21 electrical connection, the output shaft of motor 21 is direct or link to each other with the drive shaft of taking off and landing rotor blade 22 through a reduction gears. If the output speed of the oil engine 1 is low and not matched with the speed of the generator, one end of the driven shaft connected with the generator is connected with a speed increaser (a conventional gear speed increaser box) to increase the speed to the speed matched with the speed of the generator, and the output shaft of the speed increaser is connected with the input shaft of the generator. As shown in fig. 2. In specific implementation, under the same parameter conditions of FIG. 1, the weight of the used motor + generator + inverter + speed increaser (reducer) does not exceed 25 kg calculated by the service life of 10000 hours.
In specific implementation, when the output shaft of the motor 21 directly drives the lift rotor blade 22, the following structures can be adopted: a coaxial bevel gear is mounted on the output shaft of the motor, and a bevel gear matched with the coaxial bevel gear is mounted on the driving shaft of the lifting rotor blade 22.
In most cases, however, the output shaft of the electric motor 21 drives the lift rotor blades 22 through a speed reduction mechanism, the speed reduction mechanism includes a coupling 20, a drive bevel gear 23, a driven bevel gear 24, a spur pinion gear 15, and a spur gear 14, the output shaft of the electric motor 21 is connected to the drive bevel gear 23 through the coupling 20, the driven bevel gear 24 is engaged with the drive bevel gear 23, the central axis of the driven bevel gear 24 is coaxial with the central axis of the spur pinion gear 15, the spur gear 14 is engaged with the spur pinion gear 15, and the drive shaft of the lift rotor blades 22 is coaxial with the central axis of the spur gear 14, as shown in fig. 1.
The generator may also be connected to a storage battery via a bi-directional inverter, the storage battery providing power to the motor or onboard electrical equipment or serving as an emergency power source, and may also directly drive the lift rotor blades 22 if necessary.
Example two.
As shown in fig. 2.
A method for reducing the whole weight of a rotary wing vertical take-off and landing unmanned aerial vehicle based on oil-driven flight and electric take-off and landing comprises the steps that a take-off and landing rotor system and a front flying propeller system are divided into two independent parts, the front flying system is directly driven by an oil-driven engine through a clutch, and the engine is connected with a generator through the clutch; the lifting system is driven by a motor, and the electric quantity required by the motor during working is provided by the oil-driven engine 1 driving a generator to generate electricity. The oil-driven engine directly drives the front flying blade through one clutch on one hand and is connected with the generator through the other clutch on the other hand, the generator is connected with the vertical take-off and landing motor through a wire, and the motor drives the take-off and landing rotor blade, so that a mechanical transmission part between the oil-driven engine and the take-off and landing rotor blade is omitted, a battery pack for driving the motor is omitted, and the purpose of reducing the weight of the whole engine is achieved. In specific implementation, the motor can be connected with a main shaft of the lifting rotor blade directly or through a reduction gearbox. If the rotational speeds of the generator and the oil-driven engine do not match, the oil-driven engine can be connected to the generator through a speed increaser. The electrical schematic is shown in fig. 2. When necessary, a group of storage batteries can be added, the generator charges the storage batteries through the bidirectional inverter, the storage batteries can supply power for the airborne electrical equipment or serve as an emergency power supply, and the power can be supplied to the motor.
The utility model discloses the part that does not relate to all is the same with prior art or can adopt prior art to realize.
Claims (4)
1. A rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing comprises an oil-driven engine (1) and is characterized in that the oil-driven engine (1) is connected with a driving shaft of a driving belt pulley and a driven shaft of a belt device (3), one end of a driven shaft of the driving belt pulley and the driven shaft of the belt device (3) is connected with a driving shaft of a front flying blade (4) through a first clutch (7), the other end of the driven shaft is connected with a generator (11) through a second clutch (10), the generator (11) is electrically connected with a motor (21), and an output shaft of the motor (21) is directly connected with the driving shaft of a take-off and landing rotor blade (22) or is connected with the driving shaft; the speed reducing mechanism comprises a coupler (20), a driving bevel gear (23), a driven bevel gear (24), a straight-tooth pinion (15) and a straight-tooth gearwheel (14), an output shaft of a motor (21) is connected with the driving bevel gear (23) through the coupler (20), the driven bevel gear (24) is meshed with the driving bevel gear (23), a central shaft of the driven bevel gear (24) is coaxial with a central shaft of the straight-tooth pinion (15), the straight-tooth gearwheel (14) is meshed with the straight-tooth pinion (15), and a driving shaft of a lifting rotor blade (22) is coaxial with the central shaft of the straight-tooth gearwheel (14).
2. The unmanned aerial vehicle of claim 1, wherein the driven shaft is connected to the generator at one end thereof and is connected to a speed increaser, and an output shaft of the speed increaser is connected to an input shaft of the generator.
3. The unmanned aerial vehicle as claimed in claim 1, wherein the output shaft of the motor is provided with a coaxial bevel gear, and the drive shaft of the take-off and landing rotor blade (22) is provided with a bevel gear matched with the coaxial bevel gear.
4. The unmanned aerial vehicle of claim 1, wherein the generator is further connected to a storage battery through a bidirectional inverter, and the storage battery supplies power to the motor or the onboard electrical equipment.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920832578.1U CN210102007U (en) | 2019-06-04 | 2019-06-04 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920832578.1U CN210102007U (en) | 2019-06-04 | 2019-06-04 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110091999A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure flying the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises based on oil |
| CN110091997A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure of the reduction rotary wings vertical take-off and landing drone main screw lift flown based on oil electrification |
| CN111572770A (en) * | 2020-05-18 | 2020-08-25 | 河南三和航空工业有限公司 | Rescue unmanned aerial vehicle with generator and rescue mode thereof |
-
2019
- 2019-06-04 CN CN201920832578.1U patent/CN210102007U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110091999A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure flying the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises based on oil |
| CN110091997A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure of the reduction rotary wings vertical take-off and landing drone main screw lift flown based on oil electrification |
| CN111572770A (en) * | 2020-05-18 | 2020-08-25 | 河南三和航空工业有限公司 | Rescue unmanned aerial vehicle with generator and rescue mode thereof |
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