CN210102006U - Rotary wing vertical take-off and landing unmanned aerial vehicle combining electric flight with oil-driven take-off and landing - Google Patents
Rotary wing vertical take-off and landing unmanned aerial vehicle combining electric flight with oil-driven take-off and landing Download PDFInfo
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- CN210102006U CN210102006U CN201920832574.3U CN201920832574U CN210102006U CN 210102006 U CN210102006 U CN 210102006U CN 201920832574 U CN201920832574 U CN 201920832574U CN 210102006 U CN210102006 U CN 210102006U
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Abstract
The utility model provides an electronic flight and oil move rotary wing VTOL unmanned aerial vehicle that takes off and land that combines together, it includes oil-driven engine (1), characterized by oil-driven engine (1) link to each other with the driving shaft of driving and driven band pulley and belt means (3), the driven shaft one end of driving and driven band pulley and belt means (3) links to each other with the drive shaft of taking off and land rotor blade (4) through first clutch (24), the other end passes through second clutch (27) and links to each other with generator (28), generator (28) and motor (15) electrical connection, the output shaft of motor (15) passes through shaft coupling (14) and links to each other with the drive shaft of preceding flight blade (11). 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 electronic flight and oil move the rotor VTOL unmanned aerial vehicle that takes off and land combined together.
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 utilized to provide power in a take-off stage, and an oil engine is utilized to drive 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 an electronic flight and oil move rotary wing VTOL unmanned aerial vehicle that takes off and land and combine 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 the problem that complete machine weight influences flight performance greatly.
The technical scheme of the utility model is that:
the utility model provides an electronic flight and oil move rotary wing VTOL unmanned aerial vehicle that takes off and land that combines together, it includes oil-driven engine 1, characterized by 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 taking off and land rotor blade 4 through first clutch 24, and the other end passes through second clutch 27 and links to each other with generator 28, generator 28 and motor 15 electrical connection, the output shaft of motor 15 passes through shaft coupling 14 and links to each other with the drive shaft of preceding rotor blade 11.
One end of the driven shaft connected with the generator 28 is connected with a speed increaser, and an output shaft of the speed increaser is connected with an input shaft of the generator.
One end of a driven shaft of the driving and driven belt pulley and belt device 3 is connected with a driving shaft of the lifting rotor blade 4 through a first clutch 24 and a speed reducing mechanism, the speed reducing mechanism comprises a driving bevel gear 5, a driven bevel gear 6, a straight-tooth pinion 19 and a straight-tooth bull gear 18, the driven shaft of the driving and driven belt pulley and belt device 3 is connected with the driving bevel gear 5, the driven bevel gear 6 is meshed with the driving bevel gear 5, a central shaft of the driven bevel gear 6 is coaxial with a central shaft of the straight-tooth pinion 19, the straight-tooth bull gear 18 is meshed with the straight-tooth pinion 19, and the driving shaft of the lifting rotor blade 4 is coaxial with the central shaft of the straight-tooth bull gear.
The output shaft of the motor is connected with the input shaft of the speed reducer, and the output shaft of the speed reducer is connected with the driving shaft of the front fly blade 11.
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 motor shaft coupling to directly drive, and simultaneously the oil-driven engine is connected with a generator through the clutch; the lifting system is directly driven by the oil-driven engine, and the electric quantity required by the working of the motor is provided after the oil-driven engine 1 drives the generator 28 to generate electricity. The two systems are mutually independent, a large number of mechanical connection parts are omitted, meanwhile, the motor of the front flying system does not need to be powered by a storage battery, and only needs to be directly powered by a power line connected with the generator 28 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-a hydrodynamic engine, 2-a deep groove ball bearing, 3-a main driven pulley and a belt, 4-a take-off and landing rotor blade, 5-a driving bevel gear, 6-a driven bevel gear, 7-a first clutch of a tapered roller bearing, 8-a tapered roller bearing, 9-a tapered roller bearing, 10-a deep groove ball bearing, 11-a front fly blade, 12-a deep groove ball bearing, 13-a deep groove ball bearing, 14-a coupler, 15-a motor, 16-a tapered roller bearing, 17-a deep groove ball bearing, 18-a straight gear wheel, 19-a straight pinion gear, 20-a deep groove ball bearing, 21-a deep groove ball bearing, 22-a tapered roller bearing, 23-a tapered roller bearing, 24-a first clutch, 25-a tapered roller bearing, 26-tapered roller bearing, 27-second clutch, 28 generator.
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 unmanned aerial vehicle that takes off and land perpendicularly of rotary wing that electronic flight and oily combination of taking off and land, it includes oily engine 1, oily engine 1 link to each other with the driving shaft of driving and driven band pulley and belt assembly 3, driving shaft one end of driving and driven band pulley and belt assembly 3 links to each other with the drive shaft of taking off and land rotor blade 4 through first clutch 24, the other end passes through second clutch 27 and links to each other with generator 28, generator 28 and motor 15 electrical connection, motor 15's output shaft passes through shaft coupling 14 and links to each other with the drive shaft of preceding flight paddle 11, if the motor speed is too fast, still can make the output shaft of motor link to each other with the input shaft of speed reducer, the output shaft drive shaft of rethread speed reducer preceding flight paddle 11, make preceding flight paddle rotate with the speed of setting. As shown in fig. 1, if the rotation speed of the generator is not matched with the rotation speed of the driven shaft, a speed increaser (as shown in fig. 2) may be connected to the end of the driven shaft connected to the generator 28, and an output shaft of the speed increaser (which may be implemented by a speed increasing gearbox) is connected to an input shaft of the generator. In specific implementation, one end of the driven shaft of the driving and driven pulley and belt device 3 is preferably connected to the driving shaft of the lifting rotor blade 4 through a first clutch 24 and a speed reduction mechanism, as shown in fig. 1, the speed reduction mechanism includes a driving bevel gear 5, a driven bevel gear 6, a straight-tooth pinion 19 and a straight-tooth gearwheel 18, the driven shaft of the driving and driven pulley and belt device 3 is connected to the driving bevel gear 5, the driven bevel gear 6 is engaged with the driving bevel gear 5, the central axis of the driven bevel gear 6 is coaxial with the central axis of the straight-tooth pinion 19, the straight-tooth gearwheel 18 is engaged with the straight-tooth pinion 19, and the driving shaft of the lifting rotor blade 4 is coaxial with the central axis of the straight-tooth gearwheel 18.
In addition, in the specific implementation, the generator is also connected with a storage battery through a bidirectional inverter, the storage battery supplies power for the motor or the onboard electrical equipment, as shown in fig. 2, in the specific implementation, under the same parameter conditions of fig. 1, the weight of the used motor + generator + inverter + speed increaser (reducer) is not more than 25 kg calculated by using 10000 hours of service life.
Example two.
As shown in fig. 1 and 2.
A method for reducing the whole weight of a rotary wing vertical take-off and landing unmanned aerial vehicle based on oil-driven take-off and landing and electric flight is characterized in 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 a motor, and simultaneously an oil-driven engine is connected with a generator through a clutch; the lifting system is directly driven by the oil-driven engine, and the electric quantity required by the working of the motor is provided by the driving of the generator by the oil-driven engine 1. The generator is connected with a front flying motor through a lead, and the front flying motor drives the front flying blades, so that a mechanical transmission part between the oil-driven engine and the front flying blades is omitted, a battery pack for driving the motor is omitted, and the purpose of reducing the weight of the whole machine is achieved. As shown in fig. 1.
When the device is specifically implemented, the motor can be directly connected with the front fly blade main shaft or connected with the front fly blade main shaft through a reduction box. If the rotation speeds of the generator and the oil generator are not matched, the driven shaft of the main driven belt wheel and the driven shaft of the belt device 3 can be connected with 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. The utility model provides an electronic flight and oil move rotary wing VTOL unmanned aerial vehicle that takes off and land that combines together, it includes oil-driven engine (1), characterized by oil-driven engine (1) link to each other with the driving shaft of driving and driven band pulley and belt means (3), the driven shaft one end of driving and driven band pulley and belt means (3) links to each other with the drive shaft of taking off and land rotor blade (4) through first clutch (24), the other end passes through second clutch (27) and links to each other with generator (28), generator (28) and motor (15) electrical connection, the output shaft of motor (15) passes through shaft coupling (14) and links to each other with the drive shaft of preceding flight blade (11).
2. An unmanned aerial vehicle according to claim 1, wherein the driven shaft is connected to the generator (28) at one end thereof to form a speed increaser, the output shaft of the speed increaser being connected to the input shaft of the generator.
3. The unmanned aerial vehicle of claim 1, wherein one end of a driven shaft of the driving and driven pulley and belt device (3) is connected with a driving shaft of the lifting rotor blade (4) through a first clutch (24) and a speed reduction mechanism, the speed reduction mechanism comprises a driving bevel gear (5), a driven bevel gear (6), a straight pinion gear (19) and a straight gear wheel (18), the driven shaft of the driving and driven pulley and belt device (3) is connected with the driving bevel gear (5), the driven bevel gear (6) is meshed with the driving bevel gear (5), a central shaft of the driven bevel gear (6) is coaxial with a central shaft of the straight pinion gear (19), the straight gear wheel (18) is meshed with the straight pinion gear wheel (19), and the driving shaft of the lifting rotor blade (4) is coaxial with the central shaft of the straight gear wheel (18).
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920832574.3U CN210102006U (en) | 2019-06-04 | 2019-06-04 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining electric flight with oil-driven take-off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920832574.3U CN210102006U (en) | 2019-06-04 | 2019-06-04 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining electric flight with oil-driven take-off and landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210102006U true CN210102006U (en) | 2020-02-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920832574.3U Active CN210102006U (en) | 2019-06-04 | 2019-06-04 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining electric flight with oil-driven take-off and landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210102006U (en) |
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2019
- 2019-06-04 CN CN201920832574.3U patent/CN210102006U/en active Active
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