CN106945829A - A kind of universal hinge duct double-rotor aerobat - Google Patents
A kind of universal hinge duct double-rotor aerobat Download PDFInfo
- Publication number
- CN106945829A CN106945829A CN201710239852.XA CN201710239852A CN106945829A CN 106945829 A CN106945829 A CN 106945829A CN 201710239852 A CN201710239852 A CN 201710239852A CN 106945829 A CN106945829 A CN 106945829A
- Authority
- CN
- China
- Prior art keywords
- duct
- rotor
- outer ring
- fuselage
- double
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The embodiment of the invention discloses the universal hinge duct double-rotor aerobat of one kind, it is related to aircraft field, reaction torque can be balanced, the problem of rotor pneumatic efficiency is low is solved, the requirement such as flight stability and security is met simultaneously, with pneumatic efficiency, effect and service efficiency height are manipulated, can VTOL, economy, safe, practical advantage.The present invention includes：Fuselage, motor, rotor, duct, outer ring, fuselage are symmetrical arranged in two outer rings, outer ring along long axis direction and are respectively mounted two ducts, install rotor again inside duct, rotor is driven by motor, and two rotor rotationals are in opposite direction.The present invention is applied to take photo by plane, and can also be improved to rotorcycle, and also available for anti-probably field, the small-bore antipersonnel weapon of carry is used for individual soldier under battle conditions.
Description
Technical field
The present invention relates to aircraft field, more particularly to a kind of universal hinge duct double-rotor aerobat.
Background technology
Duct aircraft is that a kind of uses install in duct rotor to provide the aircraft of lift, compared to identical size without
The rotor system of duct, the duct lip of the rotor system of this aircraft can form low-pressure area and produce extra lift.Big chi
The pneumatic efficiency of very little rotor is higher than the pneumatic efficiency of small size rotor, and blade tangential resistance can be produced during single rotor wing rotation, rotation
The wing can produce a moment of torsion in opposite direction with rotor wing rotation to fuselage, and it is anti-twisted that single large-sized rotor need to be equipped with a balance
The system of square, just can guarantee that the stability of aircraft.It is unfavorable and the whole geometry size of single large scale rotor system is larger
In carrying, and rotor is more dangerous, is not suitable for some specific regions or specific task
The problem of in order to solve stability of aircraft, the design of four rotors can be used, however, although quadrotor has
Preferable flight stability, but not only the pneumatic efficiency of rotor is relatively low, preceding winged resistance is larger, and flying speed is low, covers power more
And governing system make it that the utilization rate of energy is also very low.In the case where current battery technology does not make a breakthrough, how
Improving cruising time turns into the technical bottleneck that motor-driven quadrotor develops.
To sum up, existing multi-rotor aerocraft does not possess higher rotor pneumatic efficiency in the case where stability is higher,
And single-rotor helicopter system pneumatic efficiency is high, but stability is relatively low and maneuverability requires high, and complex structure, high stability
It can not have both with high rotor pneumatic efficiency.
The content of the invention
Embodiments of the invention provide a kind of universal hinge duct double-rotor aerobat, can be higher using large-size rotor
Pneumatic efficiency, realize the manipulation of aircraft and keep the attitude stabilization of aircraft.
To reach above-mentioned purpose, embodiments of the invention are adopted the following technical scheme that：
A kind of universal hinge duct double-rotor aerobat, including：Fuselage（1）, motor（2）, motor（3）, rotor（4）, rotor（5）、
Duct（6）, duct（7）, outer ring（8）, outer ring（9）.Fuselage（1）Outer ring is symmetrical arranged along long axis direction（8）, outer ring（9）, outer ring
（8）Interior installation duct（6）, outer ring（9）Interior installation duct（7）, duct（6）Crossbeam on rotor is installed（5）And motor（2）, contain
Road（7）Crossbeam on rotor is installed（4）And motor（3）.Rotor（4）And rotor（5）Direction of rotation is on the contrary, therefore, rotor（4）With
Rotor（5）The reaction torque that fuselage is produced can be balanced mutually respectively when rotated.
Further, duct（6）And outer ring（8）Fuselage is connected to by universal hinge form（1）On, duct（7）And outer ring
（9）Fuselage is connected to by universal hinge form（1）On, compared to the operating mechanism of conventional helicopters, the design mechanism element
Number is less, and the complexity of part is lower.Directly rotating duct inclination oar disk causes control response faster.
Further outer rings（8）It is connected to fuselage（1）On, duct（6）It is connected to outer ring（8）On;Outer ring (9) is connected to
On fuselage (1), duct (7) is connected on outer ring (9).
Further, outer ring（8）And outer ring（9）Pass through long draw（13）Connection, long draw（13）Upper connection steering wheel（10）.
Further, steering wheel（10）Control outer ring（8）And outer ring（9）Elevating movement is done, while driving outer ring（8）Interior culvert
Road（6）And outer ring（9）Interior duct（7）Pitching deflection is done, rotor disk deflection can produce the pulling force in a horizontal direction,
Fly and retreat so that being provided with before the aircraft of the rotor disk.
Further, outer ring（8）Upper installation steering wheel（15）, outer ring（9）Upper installation steering wheel（14）.
Further, steering wheel（15）Control outer ring（8）Interior duct（6）Do rolling movement, steering wheel（14）Control outer ring（9）
Interior duct（7）Do rolling movement, duct（6）And duct（7）In the same direction during deflection, aircraft does side-to-side movement, duct（6）And culvert
Road（7）Reversely during deflection, aircraft does yawing rotation.
Further, airborne equipment cabin（12）Connect and controlled motor（2）And motor（3）, pass through controlled motor（2）And electricity
Machine（3）Rotating speed realize the regulation of rotor (4) and rotor (5) pulling force.When rotor (4) and rotor (5) rotating speed are improved, in gravity side
When the lift produced is rotated to upper limb more than aircraft gross weight, aircraft fuselage（1）Rise；When rotor (4) and rotor (5) rotating speed
Decline, when gravity direction upper limb rotates the lift produced less than aircraft gross weight, aircraft fuselage（1）Decline.
Further, along fuselage（1）Y direction, in duct（6）And duct（7）Lower section is respectively installed by one group of flow deflector
（11）, aerodynamic force is produced when air-flow blows over the flow deflector of deflection, the aerodynamic force that the flow deflector below fuselage is produced is to machine
Body longitudinal axis formation side force and rolling moment, available for the lateral translation of assisting in flying device, roll guidance and stabilized flight device
Lateral and roll attitude.
Further, flow deflector（11）Section shape be symmetrical airfoil, flow deflector（11）It can be produced during deflection lateral
Flow deflector in power, the present embodiment（11）Section shape be aerofoil profile, it is high to manipulate effect, small to rotor downwash flow blocked.
The universal hinge duct double-rotor aerobat of one kind provided in an embodiment of the present invention, by two ducts of reverse drive
Rotor, cancelled each other large scale rotor wing rotation when the moment of torsion that produces so that go as course stabilization, and aircraft can be stablized and fly
OK.
Brief description of the drawings
Technical scheme in order to illustrate more clearly the embodiments of the present invention, below by to be used needed for embodiment
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for ability
For the those of ordinary skill of domain, on the premise of not paying creative work, it can also be obtained according to these accompanying drawings other attached
Figure.
Fig. 1 is a kind of structural representation of universal hinge duct double-rotor aerobat provided in an embodiment of the present invention；
Fig. 2 is a kind of polycrystalline substance schematic diagram of universal hinge duct double-rotor aerobat provided in an embodiment of the present invention；
Fig. 3 is that a kind of universal dynamical system and steerable system structure for cutting with scissors duct double-rotor aerobat in the embodiment of the present invention is shown
It is intended to；
Fig. 4 be the embodiment of the present invention in it is a kind of it is universal hinge duct double-rotor aerobat duct top view.
Wherein, 1- fuselages, 2- motors, 3- motors, 4- rotors, 5- rotors, 6- ducts, 7- ducts, 8- outer rings, 9- outer rings,
10- steering wheels, 11- flow deflectors, 12- airborne equipments cabin, 13- long draws, 14- steering wheels, 15- steering wheels.
Embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining the present invention, rather than limitation of the invention.It also should be noted that, in order to just
Part related to the present invention rather than entire infrastructure are illustrate only in description, accompanying drawing.
The embodiment of the present invention provides a kind of universal hinge duct double-rotor aerobat, as depicted in figs. 1 and 2, including fuselage 1,
Motor 2, motor 3, rotor 4, rotor 5, duct 6, duct 7, outer ring 8, outer ring 9, steering wheel 10, flow deflector 11, airborne equipment cabin 12,
Long draw 13, steering wheel 14, steering wheel 15.
It is arranged symmetrically in outer ring 8 and outer ring 9, outer ring 8 and outer ring 9 and is filled by universal hinge form along long axis direction on fuselage 1
With duct 6 and duct 7, duct 6, duct 7, outer ring 8, the outer wall axle of outer ring 9 are tubular structure, power line and steering wheel circuit edge
The crossbeam and outer ring 8 of duct 6 and duct 7, the outer wall of outer ring 9 pass through the axle center of outer wall axle.Motor 2 is arranged on the crossbeam of duct 6
On, motor 3 is arranged on the crossbeam of duct 7, and rotor 4 is installed in the top of motor 3, and rotor 5, motor 2 and motor are installed in the top of motor 2
3 connection airborne equipment cabins 12.Airborne equipment cabin 12 includes power-supply system, electronic governing system and flight control system, electronic speed regulation
The controlled motor 2 of device 12 and the driving rotor 4 of motor 3 and rotor 5 are rotated backward simultaneously, lift are produced, when rotor 4 and the rotating speed of rotor 5
Improve, when gravity direction upper limb rotates the lift produced more than aircraft gross weight, aircraft fuselage 1 rises；When rotor 4 and rotation
The rotating speed of the wing 5 declines, and when gravity direction upper limb rotates the lift produced less than aircraft gross weight, aircraft fuselage 1 declines.
Outer ring 8 and outer ring 9 are connected by long draw 13, and steering wheel 10 is installed on long draw 13, and steering wheel 10 passes through long draw 13
Elevating movement is done in driving outer ring 8 and outer ring 9.Outer ring 8 and outer ring 9 have also been respectively mounted steering wheel 15 and steering wheel 14, steering wheel 15 and rudder
Machine 14 can similarly drive outer ring 8 and outer ring 9 to do yaw motion.The pitching stability of aircraft by motor 2 and motor 3 difference
Speed, and steering wheel 15 and the driving duct 6 of steering wheel 14 and the deflection of duct 7 realize that shipping-direction stability is passed through by steering wheel 15 and steering wheel 14
Reverse drive duct 6 and duct 7 are realized.
One group of flow deflector 11 is also respectively mounted on duct 6 and the lower position of duct 7, fuselage, as shown in figure 3, leading
Flow 11 is located at below fuselage datum, and the section of flow deflector 11 is symmetrical airfoil, is deflected relative to common plate flow deflector
When need the situation of wide-angle, Airfoil Design make it that flow deflector 11 can produce larger aerodynamic force, the gas under small angle deflection
Power produces lateral control power and rolling moment for the longitudinal axis of fuselage 1.The deflection of flow deflector 11 is available for the lateral of assisting in flying device
The lateral and roll attitude of translation, roll guidance and stabilized flight device.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be defined by scope of the claims.
Claims (10)
1. a kind of universal hinge duct double-rotor aerobat, it is characterised in that including：Fuselage（1）, motor（2）, motor（3）, rotor
（4）, rotor（5）, duct（6）, duct（7）, outer ring（8）, outer ring（9）, fuselage（1）Outer ring is symmetrical arranged along long axis direction（8）、
Outer ring（9）, outer ring（8）Interior installation duct（6）, outer ring（9）Interior installation duct（7）, duct（6）Crossbeam on rotor is installed（5）
And motor（2）, duct（7）Crossbeam on rotor is installed（4）And motor（3）, rotor（4）And rotor（5）Direction of rotation is opposite.
2. the universal hinge duct double-rotor aerobat of one kind according to claim 1, it is characterised in that duct（6）Pass through hinge
Chain and outer ring（8）It is hinged, duct（7）Pass through hinge and outer ring（9）It is hinged.
3. the universal hinge duct double-rotor aerobat of one kind according to claim 2, it is characterised in that outer ring（8）It is connected to
Fuselage（1）On, duct（6）It is connected to outer ring（8）On;Outer ring (9) is connected on fuselage (1), and duct (7) is connected to outer ring (9)
On.
4. the universal hinge duct double-rotor aerobat of one kind according to claim 3, it is characterised in that outer ring（8）And outer ring
（9）Pass through long draw（13）Connection, long draw（13）Upper connection steering wheel（10）.
5. the universal hinge duct double-rotor aerobat of one kind according to claim 4, it is characterised in that steering wheel（10）Control is outer
Circle（8）And outer ring（9）Rotate and drive duct (6) and duct (7) realize pitching deflect so that realize before aircraft fly or
Retreat.
6. the universal hinge duct double-rotor aerobat of one kind according to claim 5, it is characterised in that outer ring（8）It is upper to install
Steering wheel（15）, outer ring（9）Upper installation steering wheel（14）.
7. the universal hinge duct double-rotor aerobat of one kind according to claim 6, it is characterised in that steering wheel（15）Control is outer
Circle（8）Interior duct（6）Do rolling movement, steering wheel（14）Control outer ring（9）Interior duct（7）Do rolling movement, duct（6）With
Duct（7）When rotating in same direction, fuselage（1）Flown to side, duct（6）And duct（7）When rotating backward, fuselage（1）Change boat
To.
8. the universal hinge duct double-rotor aerobat of one kind according to claim 7, it is characterised in that airborne equipment cabin（12）
Connect and controlled motor（2）And motor（3）.
9. the universal hinge duct double-rotor aerobat of one kind according to claim 8, it is characterised in that along fuselage（1）Length
Direction of principal axis, in duct（6）And duct（7）Lower section is respectively installed by one group of flow deflector（11）.
10. the universal hinge duct double-rotor aerobat of one kind according to claim 9, it is characterised in that flow deflector（11）'s
Section shape is symmetrical airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710239852.XA CN106945829A (en) | 2017-04-13 | 2017-04-13 | A kind of universal hinge duct double-rotor aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710239852.XA CN106945829A (en) | 2017-04-13 | 2017-04-13 | A kind of universal hinge duct double-rotor aerobat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106945829A true CN106945829A (en) | 2017-07-14 |
Family
ID=59475857
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710239852.XA Pending CN106945829A (en) | 2017-04-13 | 2017-04-13 | A kind of universal hinge duct double-rotor aerobat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106945829A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108883826A (en) * | 2017-08-31 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Power device and single rotor unmanned vehicle |
| CN110065629A (en) * | 2019-04-30 | 2019-07-30 | 中国科学院力学研究所 | A kind of multi-functional tilting duct unmanned vehicle |
| CN110588962A (en) * | 2018-06-13 | 2019-12-20 | 空客直升机德国有限公司 | Multi-rotor aircraft with thrust producing unit comprising aerodynamically optimized shroud |
| CN110641680A (en) * | 2018-12-18 | 2020-01-03 | 深圳市格上格创新科技有限公司 | Collapsible many rotor unmanned aerial vehicle |
| CN111232191A (en) * | 2018-11-29 | 2020-06-05 | 戴瑾 | Rotor craft using control surface to control attitude |
| CN114030645A (en) * | 2021-10-11 | 2022-02-11 | 南京航空航天大学 | Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof |
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| CN102756805A (en) * | 2011-03-29 | 2012-10-31 | 郑鹏 | Traction energy transmission type duct rotor wing fly lifter |
| CN102874408A (en) * | 2012-11-02 | 2013-01-16 | 冯小淋 | Double ducted-propeller electric manned aircraft capable of taking off and landing vertically |
| CN202848026U (en) * | 2012-09-14 | 2013-04-03 | 西北工业大学 | Thrusting device capable of balancing reaction torque |
| CN103395491A (en) * | 2013-08-07 | 2013-11-20 | 龙川 | Slotting duct propeller systems and hovercar applying same |
| CN106240809A (en) * | 2016-08-23 | 2016-12-21 | 南京航空航天大学 | Novel guide based on fanjet controls multi-rotor aerocraft and control method |
-
2017
- 2017-04-13 CN CN201710239852.XA patent/CN106945829A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102756805A (en) * | 2011-03-29 | 2012-10-31 | 郑鹏 | Traction energy transmission type duct rotor wing fly lifter |
| CN202848026U (en) * | 2012-09-14 | 2013-04-03 | 西北工业大学 | Thrusting device capable of balancing reaction torque |
| CN102874408A (en) * | 2012-11-02 | 2013-01-16 | 冯小淋 | Double ducted-propeller electric manned aircraft capable of taking off and landing vertically |
| CN103395491A (en) * | 2013-08-07 | 2013-11-20 | 龙川 | Slotting duct propeller systems and hovercar applying same |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108883826A (en) * | 2017-08-31 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Power device and single rotor unmanned vehicle |
| CN110588962A (en) * | 2018-06-13 | 2019-12-20 | 空客直升机德国有限公司 | Multi-rotor aircraft with thrust producing unit comprising aerodynamically optimized shroud |
| CN110588962B (en) * | 2018-06-13 | 2023-04-07 | 空客直升机德国有限公司 | Multi-rotor aircraft with thrust producing unit comprising aerodynamically optimized shroud |
| CN111232191A (en) * | 2018-11-29 | 2020-06-05 | 戴瑾 | Rotor craft using control surface to control attitude |
| CN110641680A (en) * | 2018-12-18 | 2020-01-03 | 深圳市格上格创新科技有限公司 | Collapsible many rotor unmanned aerial vehicle |
| CN110641680B (en) * | 2018-12-18 | 2021-07-23 | 深圳市格上格创新科技有限公司 | Collapsible many rotor unmanned aerial vehicle |
| CN110065629A (en) * | 2019-04-30 | 2019-07-30 | 中国科学院力学研究所 | A kind of multi-functional tilting duct unmanned vehicle |
| CN110065629B (en) * | 2019-04-30 | 2021-08-20 | 中国科学院力学研究所 | Multifunctional tilting duct unmanned aerial vehicle |
| CN114030645A (en) * | 2021-10-11 | 2022-02-11 | 南京航空航天大学 | Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof |
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