CN110091997A - 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 - Google Patents
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 Download PDFInfo
- Publication number
- CN110091997A CN110091997A CN201910481008.7A CN201910481008A CN110091997A CN 110091997 A CN110091997 A CN 110091997A CN 201910481008 A CN201910481008 A CN 201910481008A CN 110091997 A CN110091997 A CN 110091997A
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- shaft
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- principal
- oil
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000009347 mechanical transmission Effects 0.000 claims abstract description 4
- 238000010248 power generation Methods 0.000 claims abstract description 4
- 239000003638 chemical reducing agent Substances 0.000 claims description 6
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 210000000352 storage cell Anatomy 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000005417 food ingredient Substances 0.000 description 2
- 235000013324 preserved food Nutrition 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
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, it is characterized in that the method is that the dynamic engine of oil is made on the one hand to pass through principal and subordinate's belt wheel and belt dressing and the power generation of clutch driven generator, on the other hand landing rotor blade is driven to realize VTOL by principal and subordinate's belt wheel and belt dressing and another clutch, generator passes through winged motor before conducting wire connection, fly blade before preceding winged motor drive, to save the dynamic engine that deoils to the mechanical transmission component between preceding winged blade, motor drive battery pack is saved simultaneously, achieve the purpose that reduce main screw lift.Machine main screw lift can significantly drop in the present invention, improve flying quality.
Description
Technical field
The present invention relates to a kind of unmanned air vehicle technique, the rotary wind type unmanned helicopter of especially a kind of VTOL, specifically
Say it is a kind of method and structure for reducing rotary wings vertical take-off and landing drone main screw lift flown based on oil electrification.
Background technique
Currently, rotor blade VTOL aircraft is generallyd use the dynamic engine of oil, is driven on demand by clutch
Landing rotor system and preceding winged propeller, this transmission scheme need too many bindiny mechanism and transmission mechanism, and landing
Rotor system and preceding winged system are apart from each other, and part is relatively more, and maintenance is relative complex, and transmission system overall weight compares
Greatly.
In recent years, in order to increase raising power, the total power consumption of oil turbine is reduced, people use electronic auxiliary landing
Technical solution, takeoff phase benefit moves battery and provides power, and then utilizes the dynamic engine driving aircraft flight of oil in the flat winged stage, this
Sample can substantially reduce the power of the dynamic engine of oil, reduce engine manufacture and operating cost.But this technical solution bring is most
Big the disadvantage is that unmanned plane own wt is significantly increased, another aspect increases power consumption, reduces load capacity.
Therefore, while improving unmanned plane performance and power, reducing unmanned plane own wt is also unmanned aerial vehicle design
Important indicator is the important measures for improving unmanned plane performance.
Summary of the invention
The purpose of the present invention is winged because needing complicated machine driven system to be transmitted to power for existing unmanned plane
The problem of leading to the big influence flying quality of main screw lift at row blade and landing rotor blade, is invented and a kind of is flown based on oil electrification
Reduction rotary wings vertical take-off and landing drone main screw lift method and structure.
Technical solution of the present invention first is that:
A method of it is electrified based on oil and flies to reduce rotary wings vertical take-off and landing drone main screw lift, it is characterized in that making oil is dynamic to start
On the one hand machine passes through principal and subordinate's belt wheel and belt dressing and the power generation of clutch driven generator, on the other hand pass through principal and subordinate's belt wheel and skin
Band device and another clutch driving landing rotor blade realize VTOL, and generator connects preceding winged motor by conducting wire,
Fly blade before preceding winged motor drive, deoils dynamic engine to the mechanical transmission component between preceding winged blade to save, save simultaneously
Motor drive battery pack is gone, achievees the purpose that reduce main screw lift.
The motor is connected directly or by a reduction gearbox with preceding winged blade main shaft.
The output end of principal and subordinate's belt wheel and belt dressing is connected by a speed increaser with generator.
Technical solution of the present invention second is that:
A kind of rotary wings vertical take-off and landing drone that electronic flight is combined with the dynamic landing of oil, it includes the dynamic engine 1 of oil, special
Sign is that the dynamic engine 1 of the oil is connected with the driving shaft of principal and subordinate's movable belt pulley and belt dressing 3, principal and subordinate's movable belt pulley and belt dressing
3 driven shaft one end is connected by first clutch 24 with the drive shaft of landing rotor blade 4, and the other end passes through second clutch
27 are connected with generator 28, and generator 28 and motor 15 are electrically connected, and the output shaft of motor 15 is by shaft coupling 14 with before
The drive shaft for flying blade 11 is connected.
One end of the driven axis connection generator 28 is connected with speed increaser, the output shaft of speed increaser and generator it is defeated
Enter axis to be connected.
Driven shaft one end of principal and subordinate's movable belt pulley and belt dressing 3 is by first clutch 24 and deceleration mechanism and rises
The drive shaft for dropping rotor blade 4 is connected, and deceleration mechanism includes drive bevel gear 5, driven wheel of differential 6, spur pinion 19 and straight
The driven shaft of tooth gear wheel 18, principal and subordinate's movable belt pulley and belt dressing 3 is connected with drive bevel gear 5, driven wheel of differential 6 and initiative taper
Gear 5 is meshed, the central axis of the central axis of driven wheel of differential 6 and spur pinion 19, straight-tooth gear wheel 18 and straight-tooth
Pinion gear 19 is meshed, the drive shaft of landing rotor blade 4 and the central axis of straight-tooth gear wheel 18.
The output shaft of the motor is connected with the input shaft of speed reducer, the output shaft of speed reducer and preceding winged blade 11
Drive shaft is connected.
The generator also passes through two-way inverter and is connected with power storage cell, and power storage cell is motor or airborne electric appliance
Equipment power supply.
Beneficial effects of the present invention:
By being divided into two independent parts for landing rotor system and preceding winged propeller system, preceding winged system uses the present invention
Motor coupling directly drives, while the dynamic engine of oil connects a generator by clutch；And landing system is directly adopted
With the dynamic engine driving of oil, when electric motor operation, required electricity had the dynamic engine 1 of aforementioned oil directly to provide.Two systems are mutual
It is independent, a large amount of mechanical connection components are saved, while the motor of preceding winged system is not necessarily to storage battery power supply, and only need power supply line
The generator 28 that the dynamic engine 1 of connection oil drives directly is powered, and can mitigate the weight of aircraft power transmission system significantly in this way, this
It is very favorable for aircraft.
The method of the present invention is simple, strong operability.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention.
Fig. 2 is electrical schematic diagram of the invention.
In figure: 1- oil moves engine, 2- deep groove ball bearing, 3- principal and subordinate movable belt pulley and belt, 4- landing rotor blade, 5- master
Dynamic bevel gear, 6- driven wheel of differential, 7- tapered roller bearing first clutch, 8- tapered roller bearing, 9- tapered roller bearing,
Fly blade generator, 12- deep groove ball bearing, 13- deep groove ball bearing, 14- shaft coupling, 15- motor, 16- taper roller before 11-
Bearing, 17- deep groove ball bearing, 18- straight-tooth gear wheel, 19 spur pinions, 20- deep groove ball bearing, 21- deep groove ball bearing, 22-
Tapered roller bearing, 23- tapered roller bearing, 24- first clutch, 25- tapered roller bearing, 26- tapered roller bearing,
27- second clutch, 28 generators.
Specific embodiment
The present invention is further illustrated with reference to the accompanying drawings and examples.
Embodiment one.
As shown in Figure 1, 2.
A method of it is electrified based on oil and flies to reduce rotary wings vertical take-off and landing drone main screw lift, by by landing rotor
System and preceding winged propeller system, are divided into two independent parts, preceding winged system is directly driven using motor, while this starts
Machine connects a generator by clutch；And landing system is directly driven using the bright machine of fry dried food ingredients, when electric motor operation, is required
Electricity has the dynamic engine 1 of aforementioned oil directly to provide.The dynamic engine of oil is namely set on the one hand to pass through principal and subordinate's belt wheel and belt dressing
And the power generation of clutch driven generator, landing rotor is on the other hand driven by principal and subordinate's belt wheel and belt dressing and another clutch
Blade realizes VTOL, and generator flies blade before preceding winged motor drive, to save by flying motor before conducting wire connection
The dynamic engine of oil saves motor drive battery pack to the mechanical transmission component between preceding winged blade, reach reduce it is whole
The purpose of machine weight.As shown in Figure 1.
When it is implemented, motor can be connected directly or by a reduction gearbox with preceding winged blade main shaft.If generator with
Fry dried food ingredients motor speed mismatches, and principal and subordinate's movable belt pulley and the driven shaft of belt dressing 3 can be made to be connected with generator by a speed increaser.
Its electrical schematic diagram is as shown in Figure 2.When necessary, it can also increase by a group storage battery, generator is filled by two-way inverter for battery
Electricity, battery can power for airborne electrical equipment or use as emergency power supply, it is necessary to can also be motor.
Embodiment two.
As shown in Figure 1, 2.
A kind of rotary wings vertical take-off and landing drone that electronic flight is combined with the dynamic landing of oil, it includes the dynamic engine 1 of oil,
The oil moves engine 1 and is connected with the driving shaft of principal and subordinate's movable belt pulley and belt dressing 3, principal and subordinate's movable belt pulley and belt dressing 3
Driven shaft one end is connected by first clutch 24 with the drive shaft of landing rotor blade 4, and the other end passes through second clutch 27
It is connected with generator 28, generator 28 and motor 15 are electrically connected, and the output shaft of motor 15 is flown by shaft coupling 14 with preceding
The drive shaft of blade 11 is connected, if motor speed is too fast, also the output shaft of motor can be made to be connected with the input shaft of speed reducer,
Again by the drive shaft of winged blade 11 before the output shaft driving of speed reducer, speed rotation of the winged blade to set before making.Such as Fig. 1 institute
Show, it, can be in the specific implementation in driven axis connection generator 28 if the revolving speed of invention machine revolving speed and driven shaft mismatches
One end is connected with speed increaser (such as Fig. 2), the output shaft of speed increaser (step-up gear can be used to be realized) and generator it is defeated
Enter axis to be connected.When it is implemented, driven shaft one end of principal and subordinate's movable belt pulley and belt dressing 3 is preferably by first clutch
24 and a deceleration mechanism be connected with the drive shaft of landing rotor blade 4, as shown in Figure 1, the deceleration mechanism include master
Dynamic bevel gear 5, driven wheel of differential 6, spur pinion 19 and straight-tooth gear wheel 18, principal and subordinate's movable belt pulley and belt dressing 3 it is driven
Axis is connected with drive bevel gear 5, and driven wheel of differential 6 is meshed with drive bevel gear 5, the central axis and straight-tooth of driven wheel of differential 6
The central axis of pinion gear 19, straight-tooth gear wheel 18 are meshed with spur pinion 19, the drive shaft of landing rotor blade 4 with
The central axis of straight-tooth gear wheel 18.
In addition, power storage cell is motor when it is implemented, generator also passes through two-way inverter is connected with power storage cell
Or the power supply of airborne electrical equipment, as shown in Fig. 2, when it is implemented, under the conditions of Fig. 1 identical parameters, it is small with service life 10000
When calculate, used motor+generator+inverter+increasing (subtracts) the speed amount of thinking highly of no more than 25 kilograms.
Part that the present invention does not relate to is the same as those in the prior art or can be realized by using the prior art.
Claims (8)
1. a kind of method of the reduction rotary wings vertical take-off and landing drone main screw lift flown based on oil electrification, it is characterized in that keeping oil dynamic
On the one hand engine passes through principal and subordinate's belt wheel and belt dressing and the power generation of clutch driven generator, on the other hand pass through principal and subordinate's belt wheel
And belt dressing and another clutch driving landing rotor blade realize VTOL, generator is electronic by flying before conducting wire connection
Machine flies blade before preceding winged motor drive, to save the dynamic engine that deoils to the mechanical transmission component between preceding winged blade, simultaneously
Motor drive battery pack is saved, achievees the purpose that reduce main screw lift.
2. according to the method described in claim 1, it is characterized in that the motor is directly or by a reduction gearbox and preceding winged paddle
Leaf main shaft is connected.
3. according to the method described in claim 1, it is characterized in that the output end of principal and subordinate's belt wheel and belt dressing passes through one
Speed increaser is connected with generator.
4. the rotary wings vertical take-off and landing drone that a kind of electronic flight is combined with the dynamic landing of oil, it includes that oil is dynamic engine (1),
Be connected it is characterized in that the oil moves engine (1) with the driving shaft of principal and subordinate's movable belt pulley and belt dressing (3), principal and subordinate's movable belt pulley and
Driven shaft one end of belt dressing (3) is connected by first clutch (24) with the drive shaft of landing rotor blade (4), the other end
It is connected by second clutch (27) with generator (28), generator (28) and motor (15) are electrically connected, motor (15)
Output shaft be connected with the drive shaft of preceding winged blade (11) by shaft coupling (14).
5. unmanned plane according to claim 4, it is characterized in that one end of the driven axis connection generator (28) connects
There is speed increaser, the output shaft of speed increaser is connected with the input shaft of generator.
6. unmanned plane according to claim 4, it is characterized in that the driven shaft of principal and subordinate's movable belt pulley and belt dressing (3)
One end is connected by first clutch (24) and deceleration mechanism with the drive shaft of landing rotor blade (4), and deceleration mechanism includes master
Dynamic bevel gear (5), driven wheel of differential (6), spur pinion (19) and straight-tooth gear wheel (18), principal and subordinate's movable belt pulley and belt dressing
(3) driven shaft is connected with drive bevel gear (5), and driven wheel of differential (6) is meshed with drive bevel gear (5), driven wheel of differential
(6) central axis of central axis and spur pinion (19), straight-tooth gear wheel (18) are meshed with spur pinion (19),
The drive shaft of landing rotor blade (4) and the central axis of straight-tooth gear wheel (18).
7. unmanned plane according to claim 4, it is characterized in that the input shaft of the output shaft of the motor and speed reducer
It is connected, the output shaft of speed reducer is connected with the drive shaft of preceding winged blade (11).
8. unmanned plane according to claim 4, it is characterized in that the generator also passes through two-way inverter and electric power storage electricity
Pond is connected, and power storage cell is that motor or airborne electrical equipment are powered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910481008.7A CN110091997A (en) | 2019-06-04 | 2019-06-04 | 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910481008.7A CN110091997A (en) | 2019-06-04 | 2019-06-04 | 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 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110091997A true CN110091997A (en) | 2019-08-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910481008.7A Pending CN110091997A (en) | 2019-06-04 | 2019-06-04 | 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 |
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| CN (1) | CN110091997A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112340032A (en) * | 2020-11-18 | 2021-02-09 | 武汉纺织大学 | Hybrid four-duct manned aircraft |
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| CN205418106U (en) * | 2015-12-17 | 2016-08-03 | 北京猎鹰无人机科技有限公司 | Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle |
| CN107244415A (en) * | 2017-05-24 | 2017-10-13 | 彩虹无人机科技有限公司 | The composite power rotor wing unmanned aerial vehicle that a kind of fuselage can vert |
| CN109606701A (en) * | 2018-11-27 | 2019-04-12 | 南京灵龙旋翼无人机***研究院有限公司 | A kind of the oil electric mixed dynamic matching process and system of rotary-wing aircraft |
| CN210102007U (en) * | 2019-06-04 | 2020-02-21 | 南京灵龙旋翼无人机***研究院有限公司 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
-
2019
- 2019-06-04 CN CN201910481008.7A patent/CN110091997A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205418106U (en) * | 2015-12-17 | 2016-08-03 | 北京猎鹰无人机科技有限公司 | Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle |
| CN107244415A (en) * | 2017-05-24 | 2017-10-13 | 彩虹无人机科技有限公司 | The composite power rotor wing unmanned aerial vehicle that a kind of fuselage can vert |
| CN109606701A (en) * | 2018-11-27 | 2019-04-12 | 南京灵龙旋翼无人机***研究院有限公司 | A kind of the oil electric mixed dynamic matching process and system of rotary-wing aircraft |
| CN210102007U (en) * | 2019-06-04 | 2020-02-21 | 南京灵龙旋翼无人机***研究院有限公司 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112340032A (en) * | 2020-11-18 | 2021-02-09 | 武汉纺织大学 | Hybrid four-duct manned aircraft |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190806 |
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