CN105905291A - Multi-rotor craft with tilting rotors - Google Patents
Multi-rotor craft with tilting rotors Download PDFInfo
- Publication number
- CN105905291A CN105905291A CN201610386679.1A CN201610386679A CN105905291A CN 105905291 A CN105905291 A CN 105905291A CN 201610386679 A CN201610386679 A CN 201610386679A CN 105905291 A CN105905291 A CN 105905291A
- Authority
- CN
- China
- Prior art keywords
- rotor
- tilting
- attitude
- rotors
- aerocraft
- 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
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 230000005540 biological transmission Effects 0.000 claims description 8
- 230000000694 effects Effects 0.000 claims description 6
- 239000000446 fuel Substances 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 5
- 230000004044 response Effects 0.000 description 4
- 108010066057 cabin-1 Proteins 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000008447 perception Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004899 motility Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
-
- B64D27/026—
Abstract
The invention provides a multi-rotor craft with tilting rotors. The design of the tilting rotors, a lifting body cabin and oil-electricity hybrid power is adopted. Posture rotors are driven by motors and can rotate in the same direction and by the same angle under the action of a rotor tilting mechanism. The wing-type appearance is adopted by the lifting body cabin, part of or all lift force can be provided during flying. The multi-rotor craft further comprises one or more power rotors driven by a fuel engine. The multi-rotor craft has the beneficial effects that the rotors tilt, during flying, the cabin inclination angle is small, resistance is small, loaded objects are stable, and a higher flying speed can be conveniently obtained; the flying efficiency is higher due to the fact that the lifting body cabin can provide extra lift force; the same-direction and same-angle setting is adopted when the rotors tilt, so that the flying control logic is clearer, and flying stability is facilitated; and the power rotors are driven by the fuel engine, so that the time of endurance is longer, and the load capacity is higher.
Description
Technical field
The present invention relates to vehicle technology field, particularly relate to a kind of tilting rotor multi-rotor aerocraft.
Background technology
The aircraft that multi-rotor aerocraft is a kind of simple in construction, manipulation is flexible, flight attitude is stable.Have benefited from recent years
Microprocessor, the development of sensor technology, multi-rotor aerocraft is widely used in the field such as model plane, aerial photographing platform.Many
Rotor craft passes through various kinds of sensors perception state of flight, and sends rotary speed instruction by microprocessor to rotor motor and adjust
The different flight attitudes of whole aircraft.
At present, the rotor of multi-rotor aerocraft and fuselage mostly are fixed connection structure.Need when flying before aircraft to reverse fuselage
Obtain forward direction component.This mode brings three drawback 1 fuselage torsions that loaded article can be driven to link, and is unfavorable for goods or equipment
Stability.2 fuselage torsions can increase flight resistance face, increases power consumption, is unfavorable for obtaining at a high speed.3 adjust flight attitude needs whole
Individual fuselage reverses, and motility is poor, increases power consumption.When the above drawback is less at multi-rotor aerocraft build, speed is relatively low
Inconspicuous, once aircraft volume is relatively big, and when needing to obtain higher flight speed, such as manned vehicle will be obvious.
Additionally, multi-rotor aerocraft wants to obtain stable flight attitude, need various kinds of sensors accurate perception aircraft
State, and send rotary speed instruction by microprocessor to response speed rotor motor quickly and keep state of flight stable, this
Individual process needs the reaction of each parts very fast, and aircraft could be kept stable.Wherein, sensor, processor, motor are required for
Battery is powered, and the motor power consumption particularly providing power is maximum.Being confined to current battery state-of-art, use battery is
Multi-rotor aerocraft universal cruising time of power is short, load capacity is little, which greatly limits the performance table of multi-rotor aerocraft
Now and application.For solving short shortcoming in multi-rotor aerocraft cruising time, people consider by engine fuel as dynamic
Power.But engine fuel is compared with motor, maximum shortcoming is exactly that response speed is slow, and this cannot meet the many rotors of control rapidly and fly
The requirement of row device flight attitude.
Summary of the invention
It is an object of the invention to provide a kind of tilting rotor multi-rotor aerocraft to continue compared to tradition multi-rotor aerocraft
Boat ability is higher, load capacity is bigger, flight speed faster, flight attitude more stable.
The present invention provides a kind of tilting rotor multi-rotor aerocraft, including attitude rotor, rotor inclining rotary mechanism, cabin, machine
Carry equipment box, it is characterised in that:
Described attitude rotor quantity is four or more, motor drive, and all attitude rotors pass through rotor inclining rotary mechanism
It is connected to fuselage, can vert with angle in the same direction under rotor inclining rotary mechanism effect.
Further, also including that one or more power rotor is driven by electromotor, described power rotor can be same with attitude rotor
Vert to same angle or be vertically fixedly installed in fuselage or level is fixedly installed in fuselage.
Further, described cabin uses lifting body structure, can provide all or part of lift during flight.
Further, described rotor inclining rotary mechanism is steering wheel direct-connected attitude rotor or steering wheel transmission mechanically control
Attitude rotor, or manual manipulation mechanical drive mode control attitude rotor.
Further, described mechanical system includes gear drive or belt transmission or hinge linkage transmission.
Further, described power rotor is coaxial double-oar form.
Further, at afterbody, vertical tail is installed.
Compared with prior art, the multi-rotor aerocraft of the present invention has the characteristics that and advantage:
1, the tilting rotor multi-rotor aerocraft of the present invention, obtains rotor by the way of tilting rotor rather than the fuselage that verts and divides
Power, makes aircraft more stable.
2, the tilting rotor multi-rotor aerocraft of the present invention, obtains rotation by the way of tilting rotor rather than the fuselage that verts
Wing component, advantageously reduces aircraft flight resistance thus obtains higher flight speed.
3, the tilting rotor multi-rotor aerocraft of the present invention, obtains rotation by the way of tilting rotor rather than the fuselage that verts
Being adjusted flexibly of wing component, beneficially flight attitude, reduces power consumption.
4, the tilting rotor multi-rotor aerocraft of the present invention, in that context it may be convenient to realize armstrong's patent manipulation rotor wing rotation angle
Control heading and flight speed, be conducive to simplifying manned vehicle structure and flying to control programming, improve aircraft and fly
Row safety.
5, the tilting rotor multi-rotor aerocraft of the present invention, uses oil electric mixed dynamic can realize long continuation of the journey heavy load.
6, the tilting rotor multi-rotor aerocraft of the present invention, uses lifting body cabin, can provide part or all of during flight
Lift, flight efficiency is higher.Cabin itself uses airfoil structure, compares the special fixed-wing scenario-frame of employing compact attractive in appearance,
Save space and be conducive to civil nature, universalness.Can be revolved by motor-driven attitude when the electromotor that fault rate is higher is shut down
Wing manipulation aircraft glides and force-lands, and safety is high.
7, the tilting rotor multi-rotor aerocraft of the present invention, rotor verts and uses in the same direction with the design of angle, flies to control logic
Becoming apparent from, drive mechanism is simpler.
After reading in conjunction with the accompanying the detailed description of the invention of the present invention, the other features and advantages of the invention will become more clear
Chu.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is the present invention
Some embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to according to
These accompanying drawings obtain other accompanying drawing.
Fig. 1 is the axonometric chart of a kind of tilting rotor multi-rotor aerocraft in the embodiment of the present invention 1；
Fig. 2 is the cut-away view of a kind of tilting rotor multi-rotor aerocraft in the embodiment of the present invention 1；
Wherein,
1, cabin, 2, power rotor, 3, attitude rotor, 4, gear bar, 5, rotor shaft gear, 6, rotor shaft, 7, bearing, 8,
Frame, 9, vertical tail, 10, steering wheel gear, 11, steering wheel, 12, airborne equipment case.
Detailed description of the invention
With detailed description of the invention, the present invention is described in detail below in conjunction with the accompanying drawings.
Such as Fig. 1, shown in Fig. 2, the present embodiment provides a kind of tilting rotor multi-rotor aerocraft, including cabin 1, cabin 1, sets
It is calculated as lifting body profile, flat can produce lift when flying thus obtain higher flight efficiency.Cabin 1 assembling is installed on support 8, props up
Frame 8 two ends be provided with bearing 7, by bearing 7, be connected with rotor shaft 6, be provided with rotor shaft gear 5, two ends in the middle of rotor shaft 6
Connecting dynamic rotor 2 and attitude rotor 3, power rotor are driven by electromotor, attitude rotor is driven by motor.At cabin tail
Portion is provided with vertical tail 9, vertical rotor 9 latter half rotatable, play the effect of assisted diversion and steady course.Such as Fig. 2 institute
Show, in cabin, be provided with airborne equipment case 12, airborne equipment case 12, be integrated with control chamber, fuel tank and battery case.Control chamber is provided with
Fly to control processor and sensor, be used for handling rotor rotating speed, rotor corner, vertical tail corner.Rotation of verting it is additionally provided with in cabin
Wing mechanism, is rotated by flying control control steering wheel 11, and steering wheel 11 drives steering wheel gear 10, steering wheel gear 10 and gear bar 4 engaged transmission,
Gear bar drives rotor shaft 6 with rotor shaft gear 5, engaged transmission, rotates simultaneously, then drives two ends power rotor 2 and attitude rotation
3, the most same to angular turn.
Flight control principle:
1 takes off:
Power rotor 2 and attitude rotor 3 are in vertical position.Power rotor 2 fly control control be issued to higher stablizing
Rotating speed, its lift provided is close but is less than and makes lift needed for aircraft takeoff.Start to open flying to control attitude rotor under control
It is dynamic, as long as a less lift aircraft will take off.Because engine response speed is relatively slow, so power rotor turns after taking off
Speed keeps constant.Attitude rotor is driven fast response time by motor, is responsible for main pose adjustment function.During flight, energy consumption is main
To overcome terrestrial gravitation, the fuel engines that energy density is high the power rotor-borne driven.Serve load capacity big, continuous
The effect of ETS estimated time of sailing length.Adjust fast changing flight attitude by the motor-driven attitude rotor-borne quickly responded, play
Flight stability, act on flexibly.
2 low-speed operations:
During low-speed operations, four motor-driven attitude rotors 3, be equivalent to traditional electronic four-axle aircraft, rise, decline,
Pitching, control of sideward roll principle are identical.
3 high-speed flights:
Aircraft by low speed to high-speed flight status transition time, fly control and control rotor inclining rotary mechanism and allow all attitude rotors, power
There is verting with angle in the same direction in rotor.Each rotor strengthens pulling force, keeps vertical direction pulling force constant just can holding to fly
Line height.Horizontal component can make aircraft obtain onward impulse.Obtain because the acquisition of advance component is tilting rotor, fuselage
Need not vert, during high-speed flight, resistance can greatly reduce.Along with flight speed is more and more higher, the cabin of lifting body structure starts
Produce lift.Along with the raising of flight speed, the lift that cabin provides ratio in total life is increasing, and rotor verts
Angle is increasing, until perfectly level degree, aircraft becomes closer to the state of fixed wing airplane flight.So flying
Line efficiency, flight speed is significantly better than traditional multi-rotor aerocraft.When high-speed flight, the effect of vertical tail the most more comes
The biggest, serve steady course, control the effect in course.
Certainly, described above is not limitation of the present invention, and the present invention is also not limited to the example above, and this technology is led
Change that the technical staff in territory is made in the essential scope of the present invention, retrofit, add or replace, also should belong to the present invention's
Protection domain.
Claims (7)
1. a tilting rotor multi-rotor aerocraft, including attitude rotor, rotor inclining rotary mechanism, cabin, airborne equipment case, it is special
Levy and be:
Described attitude rotor quantity is four or more, motor drive, and all attitude rotors pass through rotor inclining rotary mechanism
It is connected to fuselage, can vert with angle in the same direction under rotor inclining rotary mechanism effect.
Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: also include one or more power rotor
Being driven by electromotor, described power rotor can vert with angle in the same direction with attitude rotor or vertically be fixedly installed in fuselage or level
It is fixedly installed in fuselage.
Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: described cabin uses lifting body structure,
All or part of lift can be provided during flight.
Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: described rotor inclining rotary mechanism is that steering wheel is straight
Even attitude rotor or steering wheel transmission mechanically control attitude rotor, or manual manipulation mechanical drive mode controls attitude rotation
The wing.
Tilting rotor multi-rotor aerocraft the most according to claim 4, it is characterised in that: described mechanical system includes gear drive
Or belt transmission or hinge linkage transmission.
Tilting rotor multi-rotor aerocraft the most according to claim 2, it is characterised in that: described power rotor is coaxial double-oar shape
Formula.
Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: at afterbody, vertical end is installed
The wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610386679.1A CN105905291A (en) | 2016-06-04 | 2016-06-04 | Multi-rotor craft with tilting rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610386679.1A CN105905291A (en) | 2016-06-04 | 2016-06-04 | Multi-rotor craft with tilting rotors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105905291A true CN105905291A (en) | 2016-08-31 |
Family
ID=56743079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610386679.1A Pending CN105905291A (en) | 2016-06-04 | 2016-06-04 | Multi-rotor craft with tilting rotors |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105905291A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394895A (en) * | 2016-09-23 | 2017-02-15 | 广东天米教育科技有限公司 | Multi-form unmanned aerial vehicle and flight control method thereof |
| CN106585966A (en) * | 2016-12-13 | 2017-04-26 | 天津传承科技有限公司 | Electromechanical integration unmanned aerial vehicle device capable of smoothly taking off and landing |
| CN107972858A (en) * | 2017-12-06 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of special aircraft |
| CN108248847A (en) * | 2018-02-09 | 2018-07-06 | 北京白米科技有限公司 | Power wing body multi-rotor unmanned aerial vehicle |
| CN108572664A (en) * | 2018-06-29 | 2018-09-25 | 长沙市云智航科技有限公司 | Tilt angle detection device, control system and the method for aircraft tilting rotor |
| CN108583866A (en) * | 2018-04-12 | 2018-09-28 | 清远市巨劲科技有限公司 | A kind of unmanned plane reducing Aerodynamic intenference |
| CN108784560A (en) * | 2017-04-28 | 2018-11-13 | 蔡连锁 | Clean the unmanned plane during flying device in building |
| CN109018321A (en) * | 2018-07-02 | 2018-12-18 | 寇冠 | Driven rotor craft |
| CN111846194A (en) * | 2020-08-20 | 2020-10-30 | 叶殊钨 | Manned helicopter with multiple rotor wings |
| CN113173244A (en) * | 2021-04-09 | 2021-07-27 | 江苏大学 | Four-axis tilting wing structure and control method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2235307C (en) * | 1995-10-24 | 2006-03-14 | Hans-Jurgen Bothe | Hybrid aircraft |
| CN105292460A (en) * | 2015-10-14 | 2016-02-03 | 南昌航空大学 | Tilt-rotor based on combination of four rotor wings and fixed wing |
| CN105620716A (en) * | 2016-03-07 | 2016-06-01 | 刘海涛 | Sound insulation method for manned multi-rotor air vehicle |
| CN205668640U (en) * | 2016-06-04 | 2016-11-02 | 刘海涛 | Tilting rotor multi-rotor aerocraft |
-
2016
- 2016-06-04 CN CN201610386679.1A patent/CN105905291A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2235307C (en) * | 1995-10-24 | 2006-03-14 | Hans-Jurgen Bothe | Hybrid aircraft |
| CN105292460A (en) * | 2015-10-14 | 2016-02-03 | 南昌航空大学 | Tilt-rotor based on combination of four rotor wings and fixed wing |
| CN105620716A (en) * | 2016-03-07 | 2016-06-01 | 刘海涛 | Sound insulation method for manned multi-rotor air vehicle |
| CN205668640U (en) * | 2016-06-04 | 2016-11-02 | 刘海涛 | Tilting rotor multi-rotor aerocraft |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394895A (en) * | 2016-09-23 | 2017-02-15 | 广东天米教育科技有限公司 | Multi-form unmanned aerial vehicle and flight control method thereof |
| CN106585966A (en) * | 2016-12-13 | 2017-04-26 | 天津传承科技有限公司 | Electromechanical integration unmanned aerial vehicle device capable of smoothly taking off and landing |
| CN108784560A (en) * | 2017-04-28 | 2018-11-13 | 蔡连锁 | Clean the unmanned plane during flying device in building |
| CN107972858A (en) * | 2017-12-06 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of special aircraft |
| CN108248847A (en) * | 2018-02-09 | 2018-07-06 | 北京白米科技有限公司 | Power wing body multi-rotor unmanned aerial vehicle |
| CN108583866A (en) * | 2018-04-12 | 2018-09-28 | 清远市巨劲科技有限公司 | A kind of unmanned plane reducing Aerodynamic intenference |
| CN108572664A (en) * | 2018-06-29 | 2018-09-25 | 长沙市云智航科技有限公司 | Tilt angle detection device, control system and the method for aircraft tilting rotor |
| CN108572664B (en) * | 2018-06-29 | 2023-08-04 | 长沙市云智航科技有限公司 | Tilting angle detection device, control system and method for tilting rotor wing of aircraft |
| CN109018321A (en) * | 2018-07-02 | 2018-12-18 | 寇冠 | Driven rotor craft |
| CN111846194A (en) * | 2020-08-20 | 2020-10-30 | 叶殊钨 | Manned helicopter with multiple rotor wings |
| CN113173244A (en) * | 2021-04-09 | 2021-07-27 | 江苏大学 | Four-axis tilting wing structure and control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105905291A (en) | Multi-rotor craft with tilting rotors | |
| CN205707297U (en) | Fixed-wing unmanned plane | |
| CN101837195B (en) | Model airplane with vertical takeoff and landing | |
| US10144509B2 (en) | High performance VTOL aircraft | |
| US20200010182A1 (en) | Pivoting wing system for vtol aircraft | |
| CN106927030A (en) | A kind of oil electric mixed dynamic multi-rotor aerocraft and its flight control method | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN110267876A (en) | More rotor lift body aircrafts with tilting rotor | |
| CN107042884A (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN107140192A (en) | A kind of hybrid power unmanned plane | |
| WO2018175606A1 (en) | Vertical takeoff and landing aircraft | |
| CN103950537B (en) | The control method of displacement aircraft and control setup | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN206125421U (en) | VTOL unmanned vehicles | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN103318410A (en) | Vertical take-off and landing micro aerial vehicle without control surface | |
| CN206984354U (en) | A kind of aircraft | |
| CN206187340U (en) | Aircraft | |
| CN208915439U (en) | Adjustable wing swallow shape simulation type unmanned plane | |
| CN105173076A (en) | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) | |
| CN205668640U (en) | Tilting rotor multi-rotor aerocraft | |
| CN201744174U (en) | Model airplane vertically taking off and landing | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN107878747A (en) | A kind of Fixed Wing AirVehicle of VTOL | |
| CN207607645U (en) | Compound rotor aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160831 |