CN110091999A - 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 - Google Patents
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 Download PDFInfo
- Publication number
- CN110091999A CN110091999A CN201910481405.4A CN201910481405A CN110091999A CN 110091999 A CN110091999 A CN 110091999A CN 201910481405 A CN201910481405 A CN 201910481405A CN 110091999 A CN110091999 A CN 110091999A
- Authority
- CN
- China
- Prior art keywords
- oil
- landing
- motor
- shaft
- generator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000005611 electricity Effects 0.000 title claims abstract description 11
- 230000009347 mechanical transmission Effects 0.000 claims abstract description 4
- 230000008878 coupling Effects 0.000 claims description 6
- 238000010168 coupling process Methods 0.000 claims description 6
- 238000005859 coupling reaction Methods 0.000 claims description 6
- 210000000352 storage cell Anatomy 0.000 claims description 5
- 239000005417 food ingredient Substances 0.000 claims description 2
- 238000010248 power generation Methods 0.000 claims description 2
- 235000013324 preserved food Nutrition 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 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
- 230000008450 motivation Effects 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
Landscapes
- 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 flying the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises based on oil, it is characterized in that the method is while so that the dynamic engine of oil is on the one hand passed through winged blade before a clutch directly drives, on the other hand it is connected by another clutch with generator, generator connects VTOL motor by conducting wire, motor drive landing rotor blade, to save oil turbine to the mechanical transmission component between landing rotor blade, motor drive battery pack is saved simultaneously, achievees 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 flying the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises based on oil.
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 provides power using battery, 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, invents and a kind of fly electricity based on oil and rise
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 the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises being flown based on oil, it is characterized in that making the dynamic hair of oil
While on the one hand motivation passes through winged blade before a clutch directly drives, on the other hand pass through another clutch and generator
It is connected, generator connects VTOL motor, motor drive landing rotor blade, to save oil turbine by conducting wire
Mechanical transmission component to landing rotor blade, while motor drive battery pack is saved, reach reduction main screw lift
Purpose.
The motor is connected directly or by a reduction gearbox with landing rotor blade main shaft.
The oil moves engine and 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 the dynamic flight of oil is combined with electronic landing, 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 7 with the drive shaft of preceding winged blade 4, the other end pass through second clutch 10 and
Generator 11 is connected, and generator 11 and motor 21 are electrically connected, and the output shaft of motor 21 is directly or by a deceleration mechanism
It is connected with the drive shaft of landing rotor blade 22.
One end of the driven axis connection generator is connected with speed increaser, the input of the output shaft and generator of speed increaser
Axis is connected.
The deceleration mechanism includes shaft coupling 20, drive bevel gear 23, driven wheel of differential 24, spur pinion 15 and straight
The output shaft of tooth gear wheel 14, motor 21 is connected by shaft coupling 20 with drive bevel gear 23, driven wheel of differential 24 and active
Bevel gear 23 is meshed, the central axis of the central axis of driven wheel of differential 24 and spur pinion 15, straight-tooth gear wheel 14 with
Spur pinion 15 is meshed, the drive shaft of landing rotor blade 22 and the central axis of straight-tooth gear wheel 14.
Same shaft bevel gears are installed on the output shaft of the motor, be equipped in 22 drive shaft of landing rotor blade with
The bevel gear of the same shaft bevel gears cooperation.
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
The dynamic engine of oil directly drives through clutch, while the engine connects a generator by clutch；And landing system is adopted
With a motor drive, when electric motor operation, required electricity had the dynamic engine 1 of aforementioned oil directly to provide.Two systems phase
It is mutually independent, a large amount of mechanical connection components are saved, while the motor of landing rotor system is not necessarily to storage battery power supply, and only need
The generator 11 that the dynamic engine 1 of power supply line connection oil drives directly is powered, and can mitigate aircraft power transmission system significantly in this way
Weight, this 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, flies blade, 5- deep-groove ball before 4-
Bearing, 6- deep groove ball bearing, 7- first clutch, 8- deep groove ball bearing, 9- deep groove ball bearing, 10- second clutch, 11- hair
Motor, 12- tapered roller bearing, 13- deep groove ball bearing, 14- straight-tooth gear wheel, 15- spur pinion, 16- deep groove ball bearing,
17- deep groove ball bearing, 18- tapered roller bearing, 19- tapered roller bearing, 20- shaft coupling, 21- motor, 22- landing rotor
Blade, 23- drive bevel gear, 24- driven wheel of differential, 25- tapered roller bearing, 26- tapered roller bearing, 27- taper roller
Bearing, 28 deep groove ball bearings.
Specific embodiment
The present invention is further illustrated with reference to the accompanying drawings and examples.
Embodiment one.
As shown in Figure 2.
A method of the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises being flown based on oil, by revolving landing
Wing system and preceding winged propeller system, are divided into two independent parts, and preceding winged system is direct through clutch using the dynamic engine of oil
Driving, while the engine connects a generator by clutch；And landing system uses a motor drive, this is electronic
Machine electricity required when working 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 one
Before clutch directly drives while winged blade, on the other hand it is connected by another clutch with generator, generator is by leading
Line connect VTOL motor, motor drive landing rotor blade, thus save oil turbine to landing rotor blade it
Between mechanical transmission component, while saving motor drive battery pack, achieve the purpose that reduce main screw lift.Specific implementation
When, motor can be connected directly or by a reduction gearbox with landing rotor blade main shaft.If generator and the bright machine revolving speed of fry dried food ingredients
It mismatches, oil turbine can be made to be connected with generator by a speed increaser.Its electrical schematic diagram is as shown in Figure 2.When necessary, can also increase
Add a group storage battery, to charge the battery by two-way inverter, battery can power or make for airborne electrical equipment generator
For emergency power supply use, 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 the dynamic flight of oil is combined with electronic landing, 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 7 with the drive shaft of preceding winged blade 4, and the other end passes through second clutch 10 and power generation
Machine 11 is connected, and generator 11 and motor 21 are electrically connected, and the output shaft of motor 21 directly or by a deceleration mechanism and rises
The drive shaft for dropping rotor blade 22 is connected.If the output revolving speed of oil turbine 1 is lower, mismatches, then may be used with generator speed
Make one end of the driven axis connection generator connect a speed increaser (conventional gear gearbox) speed is increased to and is sent out
The revolving speed that motor speed matches, the output shaft of speed increaser are connected with the input shaft of generator.As shown in Figure 2.When it is implemented,
Under the conditions of Fig. 1 identical parameters, calculated with service life 10000 hours, used motor+generator+inverter+increasing (subtracting)
The speed amount of thinking highly of is no more than 25 kilograms.
When it is implemented, when the output shaft of motor 21 directly drives landing rotor blade 22, adoptable structure are as follows:
Same shaft bevel gears are installed on the output shaft of motor, are equipped in 22 drive shaft of landing rotor blade and people's shaft bevel gears
The bevel gear of cooperation.
But in most cases, the output shaft of motor 21 drives landing rotor blade 22 by deceleration mechanism, slows down
Mechanism includes shaft coupling 20, drive bevel gear 23, driven wheel of differential 24, spur pinion 15 and straight-tooth gear wheel 14, motor
21 output shaft is connected by shaft coupling 20 with drive bevel gear 23, driven wheel of differential 24 is meshed with drive bevel gear 23, from
The central axis of dynamic bevel gear 24 and the central axis of spur pinion 15, straight-tooth gear wheel 14 are nibbled with 15 phase of spur pinion
It closes, the drive shaft of landing rotor blade 22 and the central axis of straight-tooth gear wheel 14, as shown in Figure 1.
The generator can be also connected by two-way inverter with power storage cell, and power storage cell is motor or airborne electricity
Device equipment is powered or is used as emergency power supply, can also directly drive landing rotor blade 22 when necessary.
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 for flying the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises based on oil, it is characterized in that keeping oil dynamic
While on the one hand engine passes through winged blade before a clutch directly drives, on the other hand pass through another clutch and power generation
Machine is connected, and generator connects VTOL motor, motor drive landing rotor blade by conducting wire, so that it is dynamic to save fry dried food ingredients
Machine saves motor drive battery pack to the mechanical transmission component between landing rotor blade, and reaching reduces complete machine weight
The purpose of amount.
2. according to the method described in claim 1, it is characterized in that the motor is revolved directly or by a reduction gearbox and landing
Wing blade main shaft is connected.
3. according to the method described in claim 1, it is characterized in that the oil, which moves engine, passes through a speed increaser and generator phase
Even.
4. a kind of rotary wings vertical take-off and landing drone that the dynamic flight of oil is combined with electronic landing, 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 (7) with the drive shaft of preceding winged blade (4), and the other end passes through
Second clutch (10) is connected with generator (11), and generator (11) and motor (21) are electrically connected, motor (21) it is defeated
Shaft is connected directly or by a deceleration mechanism with the drive shaft of landing rotor blade (22).
5. unmanned plane according to claim 4, it is characterized in that one end of the driven axis connection generator is connected with increasing
Fast device, the output shaft of speed increaser are connected with the input shaft of generator.
6. unmanned plane according to claim 4, it is characterized in that the deceleration mechanism includes shaft coupling (20), active conical tooth
Wheel (23), driven wheel of differential (24), spur pinion (15) and straight-tooth gear wheel (14), the output shaft of motor (21) pass through connection
Axis device (20) is connected with drive bevel gear (23), and driven wheel of differential (24) is meshed with drive bevel gear (23), driven wheel of differential
(24) central axis of central axis and spur pinion (15), straight-tooth gear wheel (14) are mutually nibbled with spur pinion (15)
It closes, the drive shaft of landing rotor blade (22) and the central axis of straight-tooth gear wheel (14).
7. unmanned plane according to claim 4, it is characterized in that being equipped with same axial cone tooth on the output shaft of the motor
It takes turns, the bevel gear with the same shaft bevel gears cooperation is installed in landing rotor blade (22) drive shaft.
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 |
|---|---|---|---|
| CN201910481405.4A CN110091999A (en) | 2019-06-04 | 2019-06-04 | 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910481405.4A CN110091999A (en) | 2019-06-04 | 2019-06-04 | 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 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110091999A true CN110091999A (en) | 2019-08-06 |
Family
ID=67450208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910481405.4A Pending CN110091999A (en) | 2019-06-04 | 2019-06-04 | 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110091999A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2015137092A (en) * | 2014-01-20 | 2015-07-30 | 憲太 安田 | Parallel hybrid multi-rotor aircraft |
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| CN108238247A (en) * | 2018-02-11 | 2018-07-03 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| CN207917151U (en) * | 2018-02-07 | 2018-09-28 | 天长市星舟航空技术有限公司 | Oily electricity mixing VTOL fixed-wing unmanned plane |
| CN109606701A (en) * | 2018-11-27 | 2019-04-12 | 南京灵龙旋翼无人机系统研究院有限公司 | 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系统研究院有限公司 | 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 CN201910481405.4A patent/CN110091999A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2015137092A (en) * | 2014-01-20 | 2015-07-30 | 憲太 安田 | Parallel hybrid multi-rotor aircraft |
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| CN207917151U (en) * | 2018-02-07 | 2018-09-28 | 天长市星舟航空技术有限公司 | Oily electricity mixing VTOL fixed-wing unmanned plane |
| CN108238247A (en) * | 2018-02-11 | 2018-07-03 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| CN109606701A (en) * | 2018-11-27 | 2019-04-12 | 南京灵龙旋翼无人机系统研究院有限公司 | 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系统研究院有限公司 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20160083085A1 (en) | Electrified rotorcraft | |
| CN105644776A (en) | Multi-rotor unmanned helicopter | |
| US20210276723A1 (en) | Power assembly, power system and unmanned aerial vehicle | |
| CN108082499B (en) | Planetary hybrid helicopter power coupling system and driving method | |
| CN210102007U (en) | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing | |
| CN112810811B (en) | Double-rotor unmanned aerial vehicle | |
| CN107662702B (en) | Hybrid power double-coaxial same-side reverse tilting rotor aircraft | |
| CN103991539A (en) | Device for driving multiple rotors of airplane | |
| CN110001949A (en) | A kind of compound rotation unmanned helicopter of close coupled type | |
| CN105197232A (en) | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle | |
| CN105270619A (en) | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle | |
| CN110435883B (en) | Transmission system of parallel reverse double-rotor helicopter | |
| CN109911218A (en) | A kind of multiple-input and multiple-output dynamical system and control method for rotary-wing aircraft | |
| CN104670504A (en) | Oil/light/electricity multi-power-source fixed wing aircraft | |
| CN207374648U (en) | The double coaxial homonymy reversion tiltrotor aircrafts of hybrid power | |
| CN207791151U (en) | A kind of novel hybrid complex controll aircraft | |
| CN106741904A (en) | A kind of compound unmanned vehicle | |
| CN105035328B (en) | Hybrid-power flight vehicle | |
| CN207826569U (en) | A kind of fixed-wing formula hybrid power aircraft driving device | |
| CN110091997A (en) | 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 | |
| CN112340032A (en) | Hybrid four-duct manned aircraft | |
| CN110091999A (en) | 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 | |
| CN205440864U (en) | Unmanned helicopter of many rotors | |
| CN109606701A (en) | A kind of the oil electric mixed dynamic matching process and system of rotary-wing aircraft | |
| CN209305857U (en) | Fixed-wing electric airplane co-axial contra rotating propeller dynamical system and fixed-wing electric airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |