CN208746242U - A kind of combined type multi-rotor aerocraft - Google Patents
A kind of combined type multi-rotor aerocraft Download PDFInfo
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- CN208746242U CN208746242U CN201820756481.2U CN201820756481U CN208746242U CN 208746242 U CN208746242 U CN 208746242U CN 201820756481 U CN201820756481 U CN 201820756481U CN 208746242 U CN208746242 U CN 208746242U
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- machine body
- main machine
- slave
- combined type
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Abstract
Combined type multi-rotor aerocraft disclosed by the utility model, including host, host includes main machine body, host body is provided with battery case, the side of battery case is provided with dodge gate, dodge gate is connected by a snap with battery case, first motor is installed above battery case, first motor is connected with double-layer propeller by transmission shaft, main machine body lower part is provided with main winged control plate, the surrounding of main machine body is uniformly connected there are four identical slave, solves the problems, such as that deviated route easily occurs in existing aircraft and mission payload is low.
Description
Technical field
The utility model belongs to aeromodelling aerocraft technical field, is related to a kind of combined type multi-rotor aerocraft.
Background technique
The more gyroplanes of tradition, motor and propeller should control the lifting of fuselage, control direction and the displacement of aircraft again,
However, it is actual in-flight, any one motor go wrong can all cause course line deviate even aviation accident generation.And
And the mission payload of current more gyroplanes is very small, several hectograms just have arrived at the limit, if to promote weight bearing index
Words, the size of aircraft will great talent enough can be with, and electricity it is mechanical, electrical adjust, the weight of even battery is all problem, or even more
The extra mission payload of rotor craft carries the lithium battery for promoting self power, huge production cost and volume not enough
Also its prior art exploitation can be seriously affected, if but meet weight bearing index, the airborne period of the aircraft will be substantially reduced
And wind loading rating, also, the unmanned plane using different loads is needed in the task of execution, it not only sank money, but also reduce efficiency,
In addition, due to wing and fuselage be connected in one piece it is inseparable, carry inconvenient.
Utility model content
The purpose of the utility model is to provide a kind of combined type multi-rotor aerocrafts, solve existing aircraft and easily navigate
The problem that line deviates and mission payload is low.
The utility model is the technical scheme adopted is that a kind of combined type multi-rotor aerocraft, including host, host include
Main machine body, host body are provided with battery case, and the side of battery case is provided with dodge gate, and dodge gate and battery case pass through buckle
Connection, battery case top are equipped with first motor, and first motor is connected with double-layer propeller by transmission shaft, and main machine body lower part is set
Be equipped with it is main fly control plate, the surrounding of main machine body uniformly connect there are four identical slave.
The utility model is also characterized by
Double-layer propeller includes blade and lower blade, and lower blade is fixed on transmission shaft by lower connection valve, transmission shaft
One end far from first motor is provided with planetary gear train, and blade is fixed on planetary gear train by upper connection valve.
Balancing pole is additionally provided on the transmission shaft of upper connection valve, and balancing pole passes through the balance that is socketed on transmission shaft
Bar fixed valve is fixed, and connects column connection by double end between upper connection valve and balancing pole.
Main machine body lower part is provided with the winged control plate bracing frame of square structure, and the quadrangle for flying control plate bracing frame is connected with
The lower surface of main machine body is fixed in connecting column, connecting column one end, and the main control plate that flies is fixed on winged control plate bracing frame upper surface, flies control plate
Support frame lower surface is movably installed with camera a.
Main machine body is in " cross " structure, and four ends of main machine body are provided with the bar bucket of hollow structure, set in bar bucket
Electromagnet is installed, electromagnet is connected to main winged control plate by integral wire, and each slave includes slave body, each slave body
Tail portion is provided with electromagnet induction and turns round, and main machine body is connect by electromagnet with each slave body.
Each slave includes slave body, and slave body includes the upper housing buckled up and down and lower case, is provided in lower case
Two propellers, two propellers pass through the second motor driven respectively, are provided with direction control mechanism between two the second motors,
For controlling the inclination angle of the propeller, direction control mechanism is connected with secondary winged control plate, is additionally provided in lower case rectangular
The two sides of battery case, battery case are provided with chuck.
Direction control mechanism includes driving device and both ends are connected to the drive rod on two the second motors, and driving device
It is fixed in lower case, helical gear a is provided on drive rod, driving device one end is provided with intermeshing tiltedly with helical gear a
Gear b, pair fly the other end that control plate is fixed on driving device.
Two propellers and the second motor are located in two cylindrical holes being arranged in lower case, helical gear a and helical teeth
Wheel b is respectively positioned between two cylindrical holes, and upper housing is also accordingly opened up there are two circular hole, and two circular holes are located at two cylindrical holes
Surface.
Slave body is provided with vee tail close to the tail portion of main machine body.
The beneficial effects of the utility model are:
(1) a kind of combined type multi-rotor aerocraft realizes the lifting of aircraft by host, by slave come change of flight
Device effectively improves the stability of the aircraft of the utility model and changes the accuracy in orientation, and electromagnetism in heading
Iron connection type realize host and slave docking and isolated convenience and contraposition accuracy, under the premise of flight stability
Both can each fuselage solo hop and also be rapidly completed docking cooperation flight, with this come realize unmanned plane team property divide the work, in addition
According to the demand of load-carrying realize the separation of host and slave with combine, increase its application value, and flight operation is simple, take
Band is convenient.
(2) propeller of the main machine body of the utility model uses close coupled type double-layer propeller, and the benefit of this propeller is
Reduce the utility model aircraft pitching and yaw rotary inertia, although so that host using single rotor but still have compared with
High having a smooth flight property and biggish lift.
(3) a kind of combined type multi-rotor aerocraft of the utility model, possesses 1 super large double-layer propeller and 8 common
Propeller, combination flight stability it is higher, while can VTOL, take-off venue is saved, in addition, the entirety of the utility model
Constructional appearance is symmetrically beautiful, can be used as model plane goods of furniture for display rather than for use, widely used.
Detailed description of the invention
Fig. 1 is a kind of overall structure diagram of combined type multi-rotor aerocraft of the utility model；
Fig. 2 is the partial structure diagram of main machine body in a kind of combined type multi-rotor aerocraft of the utility model；
Fig. 3 is a kind of top view of combined type multi-rotor aerocraft of the utility model；
Fig. 4 is the structural schematic diagram of double-layer propeller in a kind of combined type multi-rotor aerocraft of the utility model；
Fig. 5 is the structural schematic diagram of planetary gear train in a kind of combined type multi-rotor aerocraft of the utility model；
Fig. 6 is the structural schematic diagram of slave in a kind of combined type multi-rotor aerocraft of the utility model.
In figure, 1. hosts, 2. main machine bodies, 3. battery cases, 4. first motors, 5. transmission shafts, 6. double-layer propellers, on 6-1.
Blade, blade under 6-2., 7. it is main fly control plates, 8. fly control plate bracing frames, 9. connecting columns, 10. camera a, 11. undercarriages, 12.
Slave, 13. dodge gates, 14. buckles, 15. heat release holes, 16. lower connection valves, 17. planetary gear trains, 17-1. sleeve, 17-2. planet
Frame, 17-3. internal gear, 17-4. external gear, connection valve on 18., 19. balancing poles, 20. balancing pole fixed valves, 21. double ends connect
Column, 22. bar buckets, 23. slave bodies, 23-1. upper housing, 23-2. lower case, the induction of 24. electromagnet are turned round, 25. propellers, and 26. the
Two motors, 27. it is secondary fly control plates, 28. driving devices, 29. drive rods, 30. helical gear a, 31. camera b, 32. cylindrical holes, 33.
Circular hole, 34. battery cases, 35.V type tail, 36. protrusions, 37. chucks.
Specific embodiment
The utility model is described in detail with reference to the accompanying drawings and detailed description.
A kind of combined type multi-rotor aerocraft of the utility model, as shown in Figure 1, including host 1, host 1 includes main machine body
2,2 top of main machine body is provided with battery case 3, and first motor 4 is equipped with above battery case, and first motor 4 is connected by transmission shaft 5
Have a double-layer propeller 6,2 lower part of main machine body be provided with it is main fly control plate 7, as shown in Fig. 2, 2 lower part of main machine body be provided with it is square
The winged control plate bracing frame 8 of structure, the quadrangle for flying control plate bracing frame 8 are connected with connecting column 9, and host is fixed in 9 one end of connecting column
The lower surface of body 2, the winged control plate bracing frame 8 of realization are stably connected with host 1, and main winged plate 7 of controlling is fixed in winged control plate bracing frame 8
Surface flies control 8 lower surface of plate bracing frame and is equipped with 360 degree of rotatable camera a10, more come visual field when guaranteeing 1 flight of host
It increases wealthy, the camera of each model can be arbitrarily installed flying control 8 lower surface of plate bracing frame, enhance the aircraft of the utility model
Extensive adaptability；Four ends of 2 lower surface of main machine body are also connected with undercarriage 11, and the undercarriage 11 is using curve elasticity
Bend pipe further improves the stability of the aircraft of the utility model to play the role of damping when taking off or landing；Such as
Shown in Fig. 1, the surrounding of main machine body 2 is uniformly connected there are four identical slave 12, and the utility model has the more of slave
Rotor craft realizes the lifting of aircraft by host 1, by slave 12 come change of flight device in heading, effectively
It improves the stability of the aircraft of the utility model and changes the accuracy in orientation, Fig. 3 is the utility model with slave
Multi-rotor aerocraft top view.
Connected as shown in Fig. 2, the side of battery case 3 is provided with dodge gate 13, dodge gate 13 and battery case 3 by buckle 14
It connects, facilitates the disassembly of battery, heat release hole 15 is offered on battery case 3, to guarantee that heat caused by battery work can be timely
Release.
As shown in figure 4, double-layer propeller 6 includes blade 6-1 and lower blade 6-2, lower blade 6-2 passes through lower connection valve
16 are fixed on transmission shaft 5, and transmission shaft 5 is provided with planetary gear train 17 far from one end of first motor 4, as shown in figure 5, planetary gear
It is 17 include the sleeve 17-1 that are socketed on transmission shaft 5, it is affixed interior there are three being connected by planet carrier 17-2 in sleeve 17-1
Gear 17-3,5 outer wall of transmission shaft are provided with external gear 17-4, and blade 6-1 is fixed on planetary gear train 17 by upper connection valve 18
Sleeve 17-1 on, due to external gear 17-4 and internal gear 17-3 steering on the contrary, making the upper leaf for being socketed in sleeve 17-1
Piece 6-1 and the lower blade 6-2 rotation direction being socketed on transmission shaft 5 on the contrary, and torque caused by rotating cancel out each other, this pair
Layer propeller 6 be close coupled type double-layer propeller, the benefit of this propeller be reduce the utility model aircraft pitching and
The rotary inertia of yaw, although so that host 1 is using single rotor but still has higher having a smooth flight property and biggish lift.
As shown in figure 4, being additionally provided with balancing pole 19 on the transmission shaft 5 of upper connection valve 18, and the balancing pole 19 passes through
The balancing pole fixed valve 20 being socketed on transmission shaft 5 is fixed, is provided with ball link on upper connection valve 18 and balancing pole 19,
The connection of column 21, balancing pole are connect by the double end that both ends are socketed in respectively on ball link between upper connection valve 18 and balancing pole 19
19 setting make the aircraft of the utility model in the descent that takes off will not because of revolving speed variation and lose stationarity.
As shown in Fig. 2, main machine body 2 provides this reality since the area of " cross " panel is larger in " cross " structure
With the novel later period can development space, four ends of main machine body 2 are provided with the bar bucket 22 of hollow structure, setting in bar bucket 22
Iron core equipped with coil package serves as electromagnet, and electromagnet is connected to main winged control plate 7 by integral wire, as shown in Figure 1, each
Slave 12 includes slave body 23, and the tail portion of each slave body 23 is provided with electromagnet induction and turns round 24, and main machine body 2 passes through electromagnet
It is connect with each slave body 23, the main variation of magnetic force for flying control plate 7 and controlling electromagnet, the connection type realizes host 1 and slave
12 docking and isolated convenience and contraposition accuracy, under the premise of flight stability both can each fuselage solo hop or
Docking cooperation flight is rapidly completed, increases its application value.
As shown in fig. 6, each slave 12 includes slave body 23, slave body 23 uses " triangle " bionical eagle moulding, secondary
Fuselage 23 includes the upper housing 23-1 and lower case 23-2 buckled up and down, propeller 25 there are two settings in lower case 23-2, and two
A propeller 25 is driven by the second motor 26, and the second motor 26 is for propeller 25 as the motor of the more gyroplanes of tradition
Power is provided, guarantees that it independently flies；It is provided with direction control mechanism between two the second motors 26, for controlling propeller 25
Inclination angle, direction control mechanism be connected with it is secondary fly control plate 27, control the operation of direction control mechanism.
As shown in fig. 6, direction control mechanism includes driving device 28 and both ends are connected to biography on two the second motors 26
Lever 29, driving device 28 uses motor, and is fixed on lower case 23-2, and helical gear a30 is provided on drive rod 29, drives
28 one end of device, which is provided with, to be driven with the intermeshing helical gear b of helical gear a30, i.e. helical gear b by driving device 28, in turn
Helical gear a30 rotation is driven, so that 29 tilt rotation of drive rod is driven, for controlling propeller 25 in flight course of slave 12
Inclination angle, direction control mechanism avoids deficiency of the slave 12 in flight course in 25 power of propeller and flexibility；Pair flies
Control plate 27 is fixed on the other end of driving device 28, and one end that pair flies control plate 27 is also connected with miniature camera b31, host 1
And GPS and camera can be all installed to guarantee the interaction between man-machine below the fuselage of slave 12.
As shown in fig. 6, two propellers 25 and the second motor 26 are located at two cylinders being arranged in lower case 23-2
In hole 32, helical gear a30 and helical gear b are respectively positioned between two cylindrical holes 32, upper housing 23-1 also accordingly open up there are two circle
Hole 33, two circular holes 33 are located at the surface of two cylindrical holes 32, realize the heat dissipation effect of entire slave 12, simultaneously
The component installation of each slave 12 is symmetrical structure, ensure that the stability of flight, while making the aircraft as model
It is more aesthetically pleasing when use.
As shown in fig. 6, being additionally provided with rectangular battery case 34 in lower case 23-2, the placement position of battery can be fixed
It sets, guarantees the steadily of centre of gravity of complete machine, the two sides of battery case 34 are provided with chuck 37, it is entangled with rubber band to fix battery,
Prevent battery from falling suddenly on the way in flight.
As shown in Figure 1, slave body 23 is provided with vee tail 35 close to the tail portion of main machine body 2, vee tail 35 reduces tail
The interference drag of the wing and fuselage, and in the case where reaching identical stability, V tail gentlier reduces fuselage weight.Entire slave
23 surface curvature of body is continuous using G3, optimizes flight parameter to the full extent, and the head visual field of slave body 23 is good, and circle is arranged
Shape protrusion 36, mountable small-sized image pickup head.
All fuselages can all use high-molecular organic material, guarantee to mitigate flight load while magnetic field is not disturbed.
By the above-mentioned means, a kind of combined type multi-rotor aerocraft of the utility model, the liter of aircraft is realized by host
Drop effectively improves the stability of the aircraft of the utility model and changes by slave come change of flight device in heading
The accuracy of variable-azimuth, and electromagnet connection type realizes the docking and isolated convenience and to level of host and slave 12
True property both each fuselage solo hop or can be rapidly completed docking cooperation flight under the premise of flight stability, be come with this real
The existing unmanned plane team property division of labor, according further to load-carrying demand realize the separation of host and slave with combine, increase its application
Value, and flight operation is simple, it is easy to carry.
Claims (9)
1. a kind of combined type multi-rotor aerocraft, which is characterized in that including host (1), the host (1) includes main machine body (2),
Main machine body (2) top is provided with battery case (3), and the side of the battery case (3) is provided with dodge gate (13), the activity
Door (13) is connect with battery case (3) by buckling (14), is equipped with first motor (4) above the battery case, first electricity
Machine (4) is connected with double-layer propeller (6) by transmission shaft (5), and main machine body (2) lower part is provided with main winged control plate (7), described
The surrounding of main machine body (2) is uniformly connected there are four identical slave (12).
2. a kind of combined type multi-rotor aerocraft as described in claim 1, which is characterized in that double-layer propeller (6) packet
Blade (6-1) and lower blade (6-2) are included, the lower blade (6-2) is fixed on transmission shaft (5) by lower connection valve (16),
The transmission shaft (5) is provided with planetary gear train (17) far from the one end of first motor (4), and upper leaf piece (6-1) passes through upper company
Valve (18) is connect to be fixed on the planetary gear train (17).
3. a kind of combined type multi-rotor aerocraft as claimed in claim 2, which is characterized in that close to the upper connection valve (18)
Transmission shaft (5) on be additionally provided with balancing pole (19), and the balancing pole (19) passes through the balancing pole that is socketed on transmission shaft (5)
Fixed valve (20) is fixed, connects column (21) connection by double end between the upper connection valve (18) and balancing pole (19).
4. a kind of combined type multi-rotor aerocraft as described in claim 1, which is characterized in that main machine body (2) lower part is set
It is equipped with the winged control plate bracing frame (8) of square structure, the quadrangle of winged control plate bracing frame (8) is connected with connecting column (9),
The lower surface of main machine body (2) is fixed in described connecting column (9) one end, and the master flies control plate (7) and is fixed on winged control plate bracing frame (8)
Upper surface, winged control plate bracing frame (8) lower surface are movably installed with camera a (10).
5. a kind of combined type multi-rotor aerocraft as described in claim 1, which is characterized in that the main machine body (2) is in " cross
Type " structure, four ends of the main machine body (2) are provided with the bar bucket (22) of hollow structure, setting in the bar bucket (22)
Equipped with electromagnet, the electromagnet is connected to the master by integral wire and flies control plate (7), and each slave (12) includes pair
Fuselage (23), the tail portion of each slave body (23) are provided with electromagnet induction and turn round (24), and the main machine body (2) passes through electromagnetism
Iron is connect with each slave body (23).
6. a kind of combined type multi-rotor aerocraft as described in claim 1, which is characterized in that each slave (12) includes
Slave body (23), the slave body (23) include the upper housing (23-1) buckled up and down and lower case (23-2), the lower case
There are two propeller (25), two propellers (25) to be driven respectively by the second motor (26) for setting in (23-2), and two
It is provided with direction control mechanism between second motor (26), for controlling the inclination angle of the propeller (25), the direction
Control mechanism is connected with secondary winged control plate (27), is additionally provided with rectangular battery case (34), institute in the lower case (23-2)
The two sides for stating battery case (34) are provided with chuck (37).
7. a kind of combined type multi-rotor aerocraft as claimed in claim 6, which is characterized in that the direction control mechanism includes
Driving device (28) and both ends are connected to the drive rod (29) on two the second motors (26), and driving device (28) is fixed on down
It on shell (23-2), is provided with helical gear a (30) on the drive rod (29), described driving device (28) one end is provided with and institute
State the intermeshing helical gear b of helical gear a (30), the secondary other end for flying control plate (27) and being fixed on driving device (28).
8. a kind of combined type multi-rotor aerocraft as claimed in claim 7, which is characterized in that two propellers (25) and
Second motor (26) is located in two cylindrical holes (32) being arranged in lower case (23-2), helical gear a (30) and helical gear b
It is respectively positioned between two cylindrical holes (32), the upper housing (23-1) also accordingly opens up there are two circular hole (33), two circles
Hole (33) is located at the surface of two cylindrical holes (32).
9. a kind of combined type multi-rotor aerocraft as described in claim 6 or 8, which is characterized in that the slave body (23) is leaned on
The tail portion of nearly main machine body (2) is provided with vee tail (35).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820756481.2U CN208746242U (en) | 2018-05-21 | 2018-05-21 | A kind of combined type multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820756481.2U CN208746242U (en) | 2018-05-21 | 2018-05-21 | A kind of combined type multi-rotor aerocraft |
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| Publication Number | Publication Date |
|---|---|
| CN208746242U true CN208746242U (en) | 2019-04-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820756481.2U Expired - Fee Related CN208746242U (en) | 2018-05-21 | 2018-05-21 | A kind of combined type multi-rotor aerocraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674644A (en) * | 2018-05-21 | 2018-10-19 | 西北工业大学明德学院 | A kind of multi-rotor aerocraft with slave |
-
2018
- 2018-05-21 CN CN201820756481.2U patent/CN208746242U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674644A (en) * | 2018-05-21 | 2018-10-19 | 西北工业大学明德学院 | A kind of multi-rotor aerocraft with slave |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190416 Termination date: 20200521 |