CN106927031A - A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor - Google Patents
A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor Download PDFInfo
- Publication number
- CN106927031A CN106927031A CN201710186049.4A CN201710186049A CN106927031A CN 106927031 A CN106927031 A CN 106927031A CN 201710186049 A CN201710186049 A CN 201710186049A CN 106927031 A CN106927031 A CN 106927031A
- Authority
- CN
- China
- Prior art keywords
- rudder face
- motor
- propeller
- unmanned aerial
- synchronizing wheel
- 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.)
- Granted
Links
- 239000004744 fabric Substances 0.000 title claims abstract description 19
- 230000005611 electricity Effects 0.000 claims abstract description 21
- 230000000694 effects Effects 0.000 claims abstract description 5
- 230000001360 synchronised effect Effects 0.000 claims abstract description 4
- 230000002195 synergetic effect Effects 0.000 claims abstract description 3
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 9
- 239000004917 carbon fiber Substances 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 7
- 230000009471 action Effects 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 5
- 230000000452 restraining effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 abstract description 9
- 238000010276 construction Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 206010000369 Accident Diseases 0.000 description 1
- 241000276425 Xiphophorus maculatus Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005457 optimization Methods 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
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/04—Adjustable control surfaces or members, e.g. rudders with compound dependent movements
-
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor, including double ducts, bi-motor, rudder face component, bi-motor is laterally vertical to be distributed in waist, power is transferred to by both sides propeller using Timing Belt and synchronizing wheel respectively, plane where the propeller rotary shaft of both sides is parallel with plane residing for bi-motor but non-coplanar；Rudder face component is located at duct lower section, pushed away by rocking arm Tiebar structure and incline, deflect rudder face to control UAV Attitude, direction, by electricity regulation and control motor speed processed, regulation unmanned plane lift and roll attitude, electricity is adjusted and steering wheel synchronous effect, double-motor power output, unified rotating speed are improved in unmanned plane VTOL, and makes bi-motor Timing Belt, synchronizing wheel, duct, the work of rudder face assembly synergistic corresponding thereto, realized that landing is steadily and at a high speed flat and navigate.Present invention symmetric configuration triangular in shape, complete machine structure good rigidity, space availability ratio is high, bi-motor it is horizontal it is vertical in put, power is transferred to by propeller using Timing Belt collaboration, double dynamical unified rotating speed, improves lift, it is ensured that landing process unmanned plane landing process is steady, simultaneously, there is one group of linkage rudder face per side propeller duct lower section, with electric tuning same-action, realize whole machine pitching, driftage, roll motion control.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, and in particular to a kind of double ducts of the horizontal cloth collaboration manipulation of bi-motor nobody
Machine.
Background technology
Unmanned plane is a kind of smaller, unmanned build, can in the air realize autonomous flight and perform certain task
Aircraft.Unmanned plane also represents because the application of its uniqueness all obtains extensive use in Military and civil fields in recent years and develops rapidly
It is an important development direction of following aviation.
In unmanned plane application process, because its is unmanned, its payload is bigger, can install more equipment and such as take the photograph
Camera is taken photo by plane or load-carrying carries out goods and materials transport, therefore, more it completes task in recent years efficiency, reliability etc., and it is right
Its structure space optimization, lift lifting and pose conversion flexibility and liter, stop, the stability of the process that falls is considered seldom, and grasp
During vertical, power transmission cooperative ability is poor, and after collision or foreign matter fly into, anti-shot ability is poor.
And known modern unmanned plane taking off, landing needs speed higher and could produce enough lift, and is to subtract
Small vibration frequency, unmanned aerial vehicle design is more likely to reduce dynamic structure quantity, causes unmanned plane when taking off, landing, and power is not
Foot, therefore, most of aircraft accidents occur in take-off and landing；For simultaneously for existing most of unmanned planes, rise
Or flying, landing needs runway, take up room, it is harsh to ground environment requirement, otherwise after using turbofan rise is gone straight up to, lead to
Crossing other thrust paddles carries out horizontal flight, and not only dynamic structure increases, in addition it is also necessary to bigger power supply, increases deadweight, knot
Structure is not compact, and the energy, space availability ratio are relatively low.
The content of the invention
The present invention proposes a kind of achievable VTOL, the culvert type unmanned plane of row two-bladed layout, using bi-motor
Horizontal cloth coordinated drive.Compared to existing many electronic unmanned planes of rotor, the characteristics of with occupying little space, each component can be realized
Harmoniously, and during landing, hovering, enough, lift is steady for power, can complete steadily to take photo by plane or to stability requirement compared with
The tasks such as the transport of small freight high.
The present invention is achieved like this, a kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor, including double ducts,
Bi-motor, rudder face component, the bi-motor is laterally vertical to be distributed in waist, and bi-motor respectively will using Timing Belt and synchronizing wheel
Power is transferred to both sides propeller, and plane where the propeller rotary shaft of both sides is parallel with plane residing for bi-motor but non-coplanar；Rudder
Face component is located at duct lower section, is pushed away by rocking arm Tiebar structure and inclines, deflects rudder face to control UAV Attitude, direction, by electricity
Regulation and control motor speed processed, adjusts unmanned plane lift and roll attitude, and electricity is adjusted and steering wheel synchronous effect, in unmanned plane VTOL
Double-motor power output, unified rotating speed are improved, and makes bi-motor Timing Belt, synchronizing wheel, duct, rudder face component corresponding thereto
Cooperate, realize that landing is steady and equal boat at a high speed.
It is preferred that the body of the unmanned plane constitutes main bearing member by the fuselage and carbon fiber pipe of carbon fiber board constitute,
Consolidate including motor mounting plate, horn fixed plate 1, horn fixed plate 2, undercarriage fixed plate, steering wheel fixed side, rudder face support tube
Fixed board, winged control installation side plate, propeller horn, rudder face support tube, undercarriage, main load-bearing part are fixed by aluminum insulated column, pipe
Folder is attached.
It is preferred that the transmission of action edge is entered in the transmission of unmanned plane by the way of synchronizing wheel adds Timing Belt, synchronization is included
Wheel, Timing Belt, tensioner idle pulley, Timing Belt is placed in propeller horn.
It is preferred that the rudder face component point row body both sides, wherein every group of rudder face component to include two panels completely the same
Aerofoil profile controls rudder face, and the motion of rudder face is connected with rudder face connecting plate by steering wheel rocking arm and oscillating bearing and pull bar using screw
The lanar four rod mechanism that constitutes of mode complete.
It is preferred that the rudder face connecting plate of the rudder face both sides, rudder face fixed plate, rudder face connecting plate and rudder face fixed plate pass through
Flange bearing is attached；It is connected with pull bar by oscillating bearing between two panels rudder face, to realize keeping strokes；Steering wheel rocking arm
The output shaft of steering wheel is fixed on by screw, when steering wheel rocking arm is rotated, rudder face realizes corresponding motion by quadric chain,
With automatically controlled coordination, the pitching of co- controlling unmanned plane, driftage, the motion in roll direction.
It is preferred that the deflection of its rudder face drives steering wheel rocking arm to deflect by steering wheel, the deflection action of steering wheel rocking arm passes through joint
Bearing and pull bar are transmitted to rudder face connecting plate, and rudder face connecting plate is fixed and can rotated around rudder face fixed plate with rudder face fixed plate；
Rudder face connecting plate is fixed with rudder face, and then drives rudder face to rotate, while being fixed on rudder face by rudder face connecting plate between two rudder faces
Fixed plate, another place is connected by oscillating bearing with pull bar, and when wherein any one rudder face rotates, another rudder face is followed
Rotate, complete the linkage deflection of rudder face.
It is preferred that the propeller horn, rudder face support tube are attached by pipe clip and body main load-bearing part.
It is preferred that described motor mounting plate and motor are by big pad and screw and motor connection, motor mounting plate, machine
Arm restraining board 1, horn fixed plate 2, undercarriage fixed plate, steering wheel fixed side, rudder face support tube fixed plate, winged control installation side plate
Between be attached by aluminum insulated column.
It is preferred that two its corresponding synchronizing wheels of motor in the bi-motor are fixed by screw, body end tensioner
Idle pulley is connected with main load-bearing part using screw, and two pieces of propeller end synchronizing wheel installing plate is connected with propeller horn by pipe clamp
Connect, tensioner idle pulley and the synchronizing wheel installing plate at propeller end are connected by screw；Synchronizing wheel installing plate is provided with flange bearing, spiral shell
Rotation oar axle is utilized after being inserted in synchronizing wheel through lower floor's synchronizing wheel installing plate flange bearing through upper strata synchronizing wheel installing plate, synchronizing wheel
Holding screw is fixed on propeller shaft；Oar folder is connected with propeller shaft, and propeller is installed on oar folder；Timing Belt is passed through
Propeller horn, is wound on two synchronizing wheels.
It is preferred that battery provides the energy for unmanned plane, electricity is streamed to electricity by the battery of duct unmanned aerial vehicle by section board
Adjust, then transmitted to winged control and motor by electricity tune, steering wheel is powered and completed by flying control；The winged control lower section goods undercarriage inner side of unmanned plane can
The corresponding load of carry, realizes task.
Compared with prior art, the advantage of the invention is that：
1. there is row two-bladed layout, stress equalization；2. there is 1 group of linkage rudder face per side propeller duct lower section, adjusted with electricity
Synergy, realizes whole machine pitching, driftage, roll motion control；3. bi-motor it is horizontal it is vertical in put, using Timing Belt collaboration by power
Propeller is transferred to, double dynamical unified rotating speed improves lift, it is ensured that landing process unmanned plane landing process is steady；4. Timing Belt
With easy tension mechanism, the elastic of Timing Belt can be suitably adjusted；5. there is the housing construction using carbon fiber board overlap joint,
Power is resisted in enhancing, mitigates deadweight；6. Timing Belt is placed in propeller horn, impedance protection, and propeller is protected by duct, is prevented
Foreign matter is invaded, it is to avoid cause flight failure.
Brief description of the drawings
Fig. 1 is front view of the invention
Fig. 2 is top view of the invention
Fig. 3 is underneath side elevation view of the invention
Fig. 4 is Section A-A partial view of the invention
Fig. 5 is side view of the invention
Fig. 6 is isometric side view of the invention
Fig. 7 is dynamical system isometric side view of the invention
Specific embodiment
The present invention is described in detail below in conjunction with the accompanying drawings.
The ground plan of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor is, horizontal to found the double electricity for being arranged in waist
Machine realizes the process that takes off vertically of unmanned plane, propeller and electricity by each self-driven propeller for being placed in both sides horn of drive mechanism
One synchronizing wheel of each connection in machine lower section, motor outputs power to propeller by Timing Belt, and the control of aspect is by being placed in
The regulation of coordinated signals rudder face and revolution speed of propeller below duct is realized.
Its specific embodiment is：
As shown in figures 1 to 6, the unmanned plane includes double duct, bi-motor, rudder face components, and the bi-motor is laterally vertical to be distributed in machine
Power is transferred to both sides propeller, both sides propeller rotary shaft by body middle part, bi-motor respectively using Timing Belt and synchronizing wheel
Place plane is parallel with plane residing for bi-motor but non-coplanar；Rudder face component is located at duct lower section, is pushed away by rocking arm Tiebar structure
Incline, deflect rudder face to control UAV Attitude, direction, 26 controlled motor rotating speeds are adjusted by electricity, adjust unmanned plane lift and roll
Attitude, electricity is adjusted and steering wheel synchronous effect, double-motor power output, unified rotating speed is improved in unmanned plane VTOL, and make double
Motor Timing Belt, synchronizing wheel, duct, the work of rudder face assembly synergistic corresponding thereto, realizes that landing is steady and equals boat, electricity at a high speed
Pond 27 provides the energy for unmanned plane, and electricity is streamed to electricity and adjusts 26 by the battery 27 of duct unmanned aerial vehicle by section board 28, then by electricity
Tune is transmitted to winged control 25 and motor 29, and steering wheel is powered and completed by flying control 25；The winged control lower section goods undercarriage inner side of unmanned plane can hang
Corresponding load is carried, task is realized.
As shown in figure 1, the body of the unmanned plane constitutes main bearing member by the fuselage and carbon fiber pipe of carbon fiber board constitute,
Including motor mounting plate 1, horn fixed plate 12, horn fixed plate 23, undercarriage fixed plate 4, steering wheel fixed side 5, rudder face branch
Stay tube fixed plate 6, winged control installation side plate 7, propeller horn 8, rudder face support tube 9, undercarriage 36.Main load-bearing part by aluminum every
It is attached from post 10, pipe clip 11.Motor mounting plate 1 is with motor 29 by big pad and screw and motor connection, motor
Installing plate 1, horn fixed plate 12, horn fixed plate 23, undercarriage fixed plate 4, steering wheel fixed side 5, rudder face support tube are fixed
It is attached by aluminum insulated column 10 between plate 6, winged control installation side plate 7.The propeller horn 8, rudder face support tube 9 pass through
Pipe clip 11 is attached with body main load-bearing part.
As shown in Figure 1 and Figure 7, the transmission of action edge is entered in the transmission of the unmanned plane by the way of synchronizing wheel adds Timing Belt,
Synchronizing wheel 12 is included, Timing Belt 13, tensioner idle pulley 14, Timing Belt is placed in propeller horn 8.Protection can be effectively played to make
With preventing Timing Belt from being transmitted by the interference effect power of foreign body, it is ensured that the safety of unmanned plane, by platy structure and culvert
Pipe protection propeller, prevents foreign matter from invading, it is to avoid cause flight failure, such as the duct 30 of duct unmanned aerial vehicle by corresponding construction with
Horn fixed plate 12 is connected, and propeller is protected by duct, prevents foreign matter from invading propeller, causes aircraft failure.
As Figure 1-4, rudder face component point row body both sides, wherein every group of rudder face component to include two panels completely the same
Aerofoil profile controls rudder face 15, and the motion of rudder face is utilized by steering wheel rocking arm 21 and oscillating bearing 22 and pull bar 23 with rudder face connecting plate 16
The lanar four rod mechanism that the mode that screw is connected is constituted is completed.Preferably, the rudder face connecting plate 16 of the both sides of the rudder face 15,
Rudder face fixed plate 17, rudder face connecting plate 16 are attached with rudder face fixed plate 17 by flange bearing 18；Lead between two panels rudder face
Cross oscillating bearing 19 to be connected with pull bar 20, to realize keeping strokes；Steering wheel rocking arm 21 is fixed on the defeated of steering wheel 24 by screw
Shaft, when steering wheel rocking arm 21 is rotated, rudder face realizes corresponding motion by quadric chain, with automatically controlled coordination, co- controlling
Unmanned plane pitching, driftage, the motion in roll direction.
Specifically, the deflection of its rudder face drives steering wheel rocking arm 21 to deflect by steering wheel 24, the deflection action of steering wheel rocking arm 21 leads to
Cross oscillating bearing 22 and pull bar 23 is transmitted to rudder face connecting plate 16, rudder face connecting plate 16 is fixed with rudder face fixed plate 17 and can be around
Rudder face fixed plate 17 is rotated；Rudder face connecting plate is fixed with rudder face 15, and then drives rudder face 15 to rotate, while leading between two rudder faces 15
Cross rudder face connecting plate 16 and be fixed on rudder face fixed plate 17, another place is connected by oscillating bearing 19 with pull bar 20, when wherein appointing
When a rudder face 15 of anticipating rotates, another rudder face 15 follows rotation, completes the linkage deflection of rudder face.
As shown in figs. 1-7, its corresponding synchronizing wheel 12 of two motors 29 in bi-motor is fixed by screw, body end
Tensioner idle pulley 14 is connected with main load-bearing part using screw, and two pieces of propeller end synchronizing wheel installing plate 31 is with propeller horn by pipe
Folder is connected, and tensioner idle pulley 14 and the synchronizing wheel installing plate 31 at propeller end are connected by screw；Synchronizing wheel installing plate 31 is installed
Pacify through upper strata synchronizing wheel after thering is flange bearing 32, propeller shaft to be inserted in synchronizing wheel through lower floor's synchronizing wheel installing plate flange bearing
Dress plate, synchronizing wheel is fixed on propeller shaft using holding screw；Oar folder 33 is connected with propeller shaft 34, and propeller 35 is pacified
Loaded on oar folder 33；Timing Belt passes through propeller horn 8, is wound on two synchronizing wheels.
Technical scheme can make unmanned plane realize following advantage using as above technical characteristic：1. have row two-bladed
Layout, stress equalization；2. have 1 group of linkage rudder face per side propeller duct lower section, and electric tuning same-action, realize whole machine pitching,
Driftage, roll motion control；3. bi-motor it is horizontal it is vertical in put, power is transferred to by propeller, double dynamical system using Timing Belt collaboration
One rotating speed, improves lift, it is ensured that landing process unmanned plane landing process is steady；4. Timing Belt has easy tension mechanism, energy
It is enough suitably to adjust the elastic of Timing Belt；5. there is the housing construction using carbon fiber board overlap joint, power is resisted in enhancing, mitigates deadweight；
6. Timing Belt is placed in propeller horn, impedance protection, and propeller is protected by duct, prevents foreign matter from invading, it is to avoid to cause to fly
Row failure.
Certainly, the present invention can also have other various embodiments, ripe in the case of without departing substantially from spirit of the invention and its essence
Know those skilled in the art and work as and various corresponding changes and deformation, but these corresponding changes and change can be made according to the present invention
Shape should all belong to the protection domain of appended claims of the invention.
Claims (12)
1. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor is manipulated, it is characterised in that including double ducts, bi-motor, rudder face
Component, the bi-motor is laterally vertical to be distributed in waist, and be transferred to for power respectively using Timing Belt and synchronizing wheel by bi-motor
Both sides propeller, plane where the propeller rotary shaft of both sides is parallel with plane residing for bi-motor but non-coplanar；Rudder face component is located at
Duct lower section, is pushed away by rocking arm Tiebar structure and inclines, deflects rudder face to control UAV Attitude, direction, and controlled motor is adjusted by electricity
Rotating speed, adjusts unmanned plane lift and roll attitude, and electricity is adjusted and steering wheel synchronous effect, and bi-motor is improved in unmanned plane VTOL
Power output, unified rotating speed, and make bi-motor Timing Belt, synchronizing wheel, duct, the work of rudder face assembly synergistic corresponding thereto,
Realize that landing is steady and equal boat at a high speed.
2. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 1 is manipulated, it is characterised in that described
The body of unmanned plane constitutes main bearing member and constitutes by the fuselage and carbon fiber pipe of carbon fiber board, including motor mounting plate (1), machine
Arm restraining board 1 (2), horn fixed plate 2 (3), undercarriage fixed plate (4), steering wheel fixed side (5), rudder face support tube fixed plate
(6), fly control installation side plate (7), propeller horn (8), rudder face support tube (9), undercarriage (36), main load-bearing part by aluminum every
It is attached from post (10), pipe clip (11).
3. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 2 is manipulated, it is characterised in that nobody
The transmission of action edge is entered in the transmission of machine by the way of synchronizing wheel adds Timing Belt, includes synchronizing wheel (12), and Timing Belt (13) rises
Tight idle pulley (14), Timing Belt is placed in propeller horn (8).
4. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 1 is manipulated, it is characterised in that described
Rudder face component point row body both sides, wherein every group of rudder face component includes the completely the same aerofoil profile of two panels and control rudder face (15), rudder
The motion in face is connected with rudder face connecting plate (16) by steering wheel rocking arm (21) and oscillating bearing (22) and pull bar (23) using screw
The lanar four rod mechanism that the mode for connecing is constituted is completed.
5. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 4 is manipulated, it is characterised in that described
The rudder face connecting plate (16) of rudder face (15) both sides, rudder face fixed plate (17), rudder face connecting plate (16) lead to rudder face fixed plate (17)
Flange bearing (18) is crossed to be attached；It is connected with pull bar (20) by oscillating bearing (19) between two panels rudder face, to realize moving
Make consistent；Steering wheel rocking arm (21) is fixed on the output shaft of steering wheel (24) by screw, and when steering wheel rocking arm (21) is rotated, rudder face leads to
Cross quadric chain and realize corresponding motion, with automatically controlled coordination, the pitching of co- controlling unmanned plane, driftage, the motion in roll direction.
6. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 5 is manipulated, it is characterised in that its rudder
The deflection in face drives steering wheel rocking arm (21) to deflect by steering wheel (24), and the deflection action of steering wheel rocking arm (21) passes through oscillating bearing (22)
Transmitted to rudder face connecting plate (16) with pull bar (23), rudder face connecting plate (16) is fixed with rudder face fixed plate (17) and can be around rudder face
Fixed plate (17) is rotated；Rudder face connecting plate is fixed with rudder face (15), and then drives rudder face (15) to rotate, one between two rudder faces (15)
Rudder face fixed plate (17) is fixed in side by rudder face connecting plate (16), and another place is connected by oscillating bearing (19) with pull bar (20)
Connect, when wherein any one rudder face (15) rotates, another rudder face (15) follows rotation, complete the linkage deflection of rudder face.
7. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 2 is manipulated, it is characterised in that described
Propeller horn (8), rudder face support tube (9) are attached by pipe clip (11) and body main load-bearing part.
8. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 2 is manipulated, it is characterised in that described
Motor mounting plate (1) and motor (29) by big pad and screw and motor connection, motor mounting plate (1), horn fixed plate 1
(2), horn fixed plate 2 (3), undercarriage fixed plate (4), steering wheel fixed side (5), rudder face support tube fixed plate (6), winged control peace
It is attached by aluminum insulated column (10) between dress side plate (7).
9. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 2 is manipulated, it is characterised in that described
The two its corresponding synchronizing wheel of motors (29) (12) in bi-motor are fixed by screw, body end tensioner idle pulley (14) with it is main
Bearing member is connected using screw, and two pieces of propeller end synchronizing wheel installing plate (31) is connected with propeller horn by pipe clamp, spiral shell
The tensioner idle pulley (14) at rotation oar end is connected by screw with synchronizing wheel installing plate (31)；Synchronizing wheel installing plate (31) is provided with flange
Bearing (32), propeller shaft is installed after being inserted in synchronizing wheel through lower floor's synchronizing wheel installing plate flange bearing through upper strata synchronizing wheel
Plate, synchronizing wheel is fixed on propeller shaft using holding screw；Oar folder (33) is connected with propeller shaft (34), propeller
(35) it is installed on oar folder (33)；Timing Belt passes through propeller horn (8), is wound on two synchronizing wheels.
10. double duct unmanned aerial vehicles that a kind of horizontal cloth collaboration of bi-motor according to claim 1 is manipulated, it is characterised in that electricity
Pond (27) provides the energy for unmanned plane, and electricity is streamed to electric tune by the battery (27) of duct unmanned aerial vehicle by section board (28)
(26), then by electricity tune transmit to winged control (25) and motor (29), steering wheel is powered and completed by flying control (25)；The winged control lower section of unmanned plane
Or undercarriage inner side can the corresponding load of carry, realize task.
A kind of 11. double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor according to claim 1, it is characterised in that machine
Body main body is two-layer carbon fiber board clamp structure, bi-motor and double ducts symmetric configuration triangular in shape, and complete machine structure good rigidity is empty
Between utilization rate it is high.
12. a kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor according to claim 1, it is characterised in that two
Individual motor drives two propeller rotationals by a set of Timing Belt and synchronizing wheel respectively, and motor is in whole propeller and duct
Top, improve the height of C.G. of whole machine, be easy to the manipulation of unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710186049.4A CN106927031B (en) | 2017-03-27 | 2017-03-27 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710186049.4A CN106927031B (en) | 2017-03-27 | 2017-03-27 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106927031A true CN106927031A (en) | 2017-07-07 |
| CN106927031B CN106927031B (en) | 2018-12-21 |
Family
ID=59425374
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710186049.4A Expired - Fee Related CN106927031B (en) | 2017-03-27 | 2017-03-27 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106927031B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107914874A (en) * | 2017-12-06 | 2018-04-17 | 佛山市神风航空科技有限公司 | A kind of four wing flapping-wing aircrafts |
| WO2019073415A1 (en) * | 2017-10-11 | 2019-04-18 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| CN113415411A (en) * | 2021-07-28 | 2021-09-21 | 涵涡智航科技(玉溪)有限公司 | Double-duct unmanned aerial vehicle |
| CN113830288A (en) * | 2021-11-09 | 2021-12-24 | 北京航空航天大学 | Control mechanism for control surface of ducted aircraft |
| CN113911330A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Oil moves duct aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005056730A1 (en) * | 2005-11-29 | 2006-09-21 | Gerd Zelck | Rotary-wing aircraft e.g. helicopter, has rolling cylinder with guide rollers, where rollers have spacers that are pivoted around central rotor arm axis in area so that section contour is selectively changed |
| CN204726665U (en) * | 2015-06-29 | 2015-10-28 | 廖其凌 | Portable and collapsible double-rotor aerobat |
| CN205396527U (en) * | 2016-03-08 | 2016-07-27 | 田春雨 | Many heligyro of letter way formula power |
| CN205524969U (en) * | 2016-04-15 | 2016-08-31 | 广州市派飞科技有限公司 | Unmanned aerial vehicle with multiple rotor wings |
| CN105947192A (en) * | 2016-06-01 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Tilting double-duct unmanned aerial vehicle |
| CN106184755A (en) * | 2016-07-28 | 2016-12-07 | 易瓦特科技股份公司 | It is applied to the drive mechanism of many rotor wing unmanned aerial vehicles |
-
2017
- 2017-03-27 CN CN201710186049.4A patent/CN106927031B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005056730A1 (en) * | 2005-11-29 | 2006-09-21 | Gerd Zelck | Rotary-wing aircraft e.g. helicopter, has rolling cylinder with guide rollers, where rollers have spacers that are pivoted around central rotor arm axis in area so that section contour is selectively changed |
| CN204726665U (en) * | 2015-06-29 | 2015-10-28 | 廖其凌 | Portable and collapsible double-rotor aerobat |
| CN205396527U (en) * | 2016-03-08 | 2016-07-27 | 田春雨 | Many heligyro of letter way formula power |
| CN205524969U (en) * | 2016-04-15 | 2016-08-31 | 广州市派飞科技有限公司 | Unmanned aerial vehicle with multiple rotor wings |
| CN105947192A (en) * | 2016-06-01 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Tilting double-duct unmanned aerial vehicle |
| CN106184755A (en) * | 2016-07-28 | 2016-12-07 | 易瓦特科技股份公司 | It is applied to the drive mechanism of many rotor wing unmanned aerial vehicles |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| WO2019073415A1 (en) * | 2017-10-11 | 2019-04-18 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| CN107914874A (en) * | 2017-12-06 | 2018-04-17 | 佛山市神风航空科技有限公司 | A kind of four wing flapping-wing aircrafts |
| CN113415411A (en) * | 2021-07-28 | 2021-09-21 | 涵涡智航科技(玉溪)有限公司 | Double-duct unmanned aerial vehicle |
| CN113415411B (en) * | 2021-07-28 | 2022-03-11 | 涵涡智航科技(玉溪)有限公司 | Double-duct unmanned aerial vehicle |
| CN113830288A (en) * | 2021-11-09 | 2021-12-24 | 北京航空航天大学 | Control mechanism for control surface of ducted aircraft |
| CN113830288B (en) * | 2021-11-09 | 2024-06-18 | 北京航空航天大学 | Control surface control mechanism of ducted aircraft |
| CN113911330A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Oil moves duct aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106927031B (en) | 2018-12-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106927031A (en) | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor | |
| US10752372B2 (en) | Aircraft | |
| CN110316370B (en) | Layout and control method of distributed power tilting wing aircraft | |
| CN105059536B (en) | Varying pitch rotor driver and multi-rotor aerocraft | |
| CN103538714A (en) | Vertical take-off and landing model aircraft unmanned aerial vehicle | |
| CN103935517B (en) | Aircraft | |
| US20180362169A1 (en) | Aircraft with electric and fuel engines | |
| US20160368597A1 (en) | Torque balanced, lift rotor module providing increased lift with few or no moving parts | |
| CN106143889A (en) | A kind of undercarriage is as the quadrotor of handgrip | |
| CN105416574B (en) | A kind of unmanned plane undercarriage | |
| CN105584629A (en) | Aircraft capable of vertically taking off and landing | |
| CN107416200A (en) | A kind of electronic compound rotor aircraft | |
| CN103552686A (en) | Combined type ducted aerial reconnaissance robot | |
| CN106379525A (en) | Wing connected unmanned plane | |
| CN108177766A (en) | Multi-rotor unmanned aerial vehicle | |
| US11247783B1 (en) | Aircraft | |
| CN106005394A (en) | Rescue aircraft | |
| CN107042883A (en) | Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading | |
| CN114715392B (en) | Variant flying wing type tilting rotor unmanned aerial vehicle | |
| CN113277062A (en) | Telescopic wing, wing interval adjusting module, aircraft and control method | |
| CN206750143U (en) | A kind of electronic compound rotor aircraft | |
| CN106275416A (en) | The composite aircraft that fixed-wing forms with many rotors | |
| CN109665097A (en) | Compound offline mode unmanned plane | |
| CN106741933A (en) | A kind of amphibious unmanned plane | |
| CN208393624U (en) | A kind of coaxial anti-paddle rotor system of culvert type |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200331 Address after: 201313 Room 118, Building 20, No. 83 Lane 1-42, Hongxiang North Road, Wanxiang Town, Pudong New Area, Shanghai Patentee after: Shanghai Luo Peng Aviation Technology Co.,Ltd. Address before: 610041 Sichuan city of Chengdu province high tech Zone Yizhou Avenue North 555 No. 1 Building 3 unit 906 Patentee before: CHENGDU R & D BRANCH, SHANGHAI LUOPENG AVIATION TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181221 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |