CN206782062U - A kind of high stability six rotorcraft - Google Patents
A kind of high stability six rotorcraft Download PDFInfo
- Publication number
- CN206782062U CN206782062U CN201720371848.4U CN201720371848U CN206782062U CN 206782062 U CN206782062 U CN 206782062U CN 201720371848 U CN201720371848 U CN 201720371848U CN 206782062 U CN206782062 U CN 206782062U
- Authority
- CN
- China
- Prior art keywords
- aileron
- central plate
- mobile jib
- gear
- motor
- 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.)
- Active
Links
- 238000005452 bending Methods 0.000 claims abstract description 9
- 238000003032 molecular docking Methods 0.000 claims description 13
- 125000006850 spacer group Chemical group 0.000 claims description 7
- 230000033228 biological regulation Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 2
- 230000005484 gravity Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 230000001737 promoting effect Effects 0.000 description 3
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model belongs to unmanned machine preparing technical field, more particularly to a kind of high stability six rotorcraft, central plate including regular hexagon, the central plate includes upper central plate and lower central plate, it is provided with the position that six ailerons are connected to six angles of regular hexagon between upper central plate and lower central plate by aileron mobile jib, aileron mobile jib is three sections of bending structures, it is furnished with propeller in aileron end, the bar segment of aileron mobile jib connection propeller is higher than the bar segment of aileron mobile jib connecting central plate, propeller is caused to promote air-flow to central plate outside after rotation.The methods of aircraft vibrates by absorbing propeller, regulation rotor angle, closing nacelle, the stability of unmanned plane during flying is improved, it is smoothly completed the task such as take photo by plane, monitor, shooting clear picture.
Description
Technical field
The utility model belongs to unmanned machine preparing technical field, and in particular to a kind of rotor flying of high stability six
Device.
Background technology
Unmanned plane be commonly used to replace the mankind perform it is various take photo by plane, monitoring task, task progress during, due to nobody
The vibration of machine propeller, the unadjustable of rotor angle, wind-force cause to take photo by plane, monitor picture to influence inside unmanned plane etc.
It is unintelligible in addition task can not be completed, therefore need a kind of high unmanned plane of stability of utility model badly.
Utility model content
In order to solve the above-mentioned technical problem, the utility model provides a kind of high stability six rotorcraft, passes through suction
The methods of receiving propeller vibration, regulation rotor angle, closing nacelle, improves the stability of unmanned plane during flying, smoothly completes it
The task such as take photo by plane, monitor, shooting clear picture.
The utility model is achieved in that a kind of high stability six rotorcraft, including：The center of regular hexagon
Plate, the central plate include upper central plate and lower central plate, be provided with six ailerons by aileron mobile jib be connected to upper central plate with
The position at six angles of regular hexagon between lower central plate, aileron mobile jib are three sections of bending structures, and aileron end is furnished with propeller,
The bar segment of aileron mobile jib connection propeller is higher than the bar segment of aileron mobile jib connecting central plate, and propeller is caused to push away after rotation
Take offence and flow on the outside of central plate.
Further, aileron is connected to the central plate of regular hexagon by aileron connector, between aileron and central plate
Angle change is controlled by angle control assembly, and aileron connector includes two parallel fixed seats, is connected to by fixed seat
Between central plate and lower central plate, two fixed seats are connected by a connecting rod in the lower rear side of two parallel fixed seats,
The angle control assembly includes motor, first gear and second gear, and second gear is rotatably mounted to the company
On extension bar, motor drives first gear to rotate, and first gear drives second gear to rotate, and second gear is controlled by rotating
The angle change of aileron.
Further, connection otic placode is set in the outer side-lower of two fixed seats, the aircraft also includes being fixedly connected
The aileron mobile jib connecting seat of aileron mobile jib, aileron mobile jib connecting seat are arranged to cylindrical structure, and the lower section both sides of cylinder have triangle
After the connection otic placode of shape, the connection otic placode of triangle and the connection otic placode of fixed seat are by a spiral shell axis connection, formed connecting seat with
Fixed seat axis connection, semicircle docking gear, docking gear and second tooth are fixedly installed in aileron mobile jib connecting seat end
Wheel fitting, second gear, which rotates, drives opposing teeth wheel to rotate, so as to drive the angle of aileron mobile jib and the central plate to become
Change.
Further, angle control assembly controls the aileron mobile jib axis and the angle of plane where the central plate to exist
Change in the range of ± 5 °.
Further, the fixed seat by screw connection between upper central plate and lower central plate.
Further, the motor and first gear are arranged on the lower central plate.
Further, aileron connects propeller by aileron mobile jib, and motor connection set, motor are connected on the aileron mobile jib
Adapter sleeve is nested into the end of aileron mobile jib, motor connection set and motor base bolt connection, and electric machine speed regulation is set in motor base
Device, motor are fixed in motor base and then are tightly connected by motor fixed cover, and fixed cover, spiral are set in motor fixed cover
Oar is screwed in motor fixed cover, and sets stop washer and stop from lower to upper between propeller and fixed cover
Pad, cover on motor and be fixedly connected with propeller by hex(agonal)screw.
Further, the position on six sides of regular hexagon sets central plate to close between the upper central plate and lower central plate
Lid.
Further, the central plate closing cap vertical section is arc.
Further, it is additionally provided with gondola below the high stability six rotorcraft.
Further, gondola is connected by gondola connecting rod with aircraft.
Further, two supports are set below high stability six rotorcraft.
Compared with prior art, the utility model has the advantage of：
1) aileron mobile jib is arranged to three sections of bending structures, declines aircraft center of gravity, improves flight stability；
2) using the angle of angle control assembly adjustment aileron, to adapt to different flying conditions, flight efficiency is improved；
3) by setting stop assembly between propeller and motor, the vibration of propeller is prevented to be delivered to aileron so as to pass
Aircraft body is passed, further improves flight stability；
4) the central plate closure that vertical section is arc is set between upper central plate and lower central plate, reduces aircraft wind
Resistance, equally improves flight stability.
Brief description of the drawings
Fig. 1 is the aircraft integrated model schematic diagram that the utility model embodiment provides；
Fig. 2 is the aircraft integrated model exploded perspective view that the utility model embodiment provides；
Fig. 3 is angle control assembly mplifying structure schematic diagram in Fig. 1；
Fig. 4 is the aircraft flap portion configuration schematic diagram that the utility model embodiment provides.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining
The utility model, it is not used to limit the utility model.
Embodiment 1,
Referring to Fig. 1, there is provided a kind of high stability six rotorcraft, including：The central plate 1 of regular hexagon, the central plate 1
Including upper central plate 101 and lower central plate 102, it is provided with six ailerons 2 and upper central plate 101 is connected to by aileron mobile jib 201
The position at six angles of regular hexagon between lower central plate 102, aileron mobile jib 201 are three sections of bending structures, and the end of aileron 2 is matched somebody with somebody
There is propeller 202, aileron mobile jib 201 connects bar segment of the bar segment higher than the connecting central plate 1 of aileron mobile jib 201 of propeller 202, made
Obtain aircraft entirety center of gravity to decline, improve flight stability, propeller 202 is caused to promote air-flow to center after rotation
The outside of plate 1, now, the lift of aircraft so as to save the efficiency of motor, while improves the time of flight to inner side.
Embodiment 2,
Referring to Fig. 1 and Fig. 2, there is provided a kind of high stability six rotorcraft, including：The central plate 1 of regular hexagon, in this
Core 1 includes upper central plate 101 and lower central plate 102, is provided with six ailerons 2 and is connected to upper center by aileron mobile jib 201
The position at six angles of regular hexagon between plate 101 and lower central plate 102, aileron mobile jib 201 are three sections of bending structures, aileron 2
End is furnished with propeller 202, and aileron mobile jib 201 connects the bar segment of propeller 202 higher than the connecting central plate 1 of aileron mobile jib 201
Bar segment so that aircraft entirety center of gravity declines, and improves flight stability, propeller 202 is after rotation, caused promotion air-flow
To the outside of central plate 1, now, the lift of aircraft is to inner side, so as to save the efficiency of motor, while improve flight when
Between；
Aileron 2 is connected to the central plate 1 of regular hexagon, the angle between aileron 2 and central plate 1 by aileron connector 203
Degree change is controlled by angle control assembly 3, and aileron connector 203 includes two parallel fixed seats 204, passes through fixed seat 204
It is connected between central plate 101 and lower central plate 102, passes through a connecting rod in the lower rear side of two parallel fixed seats 204
205 connect two fixed seats 204, and referring to Fig. 3, the angle control assembly 3 includes motor 301, the and of first gear 302
Second gear 303, second gear 302 are rotatably mounted in the connecting rod 205, and motor 301 drives first gear
302 rotate, and first gear 302 drives second gear 303 to rotate, and second gear 303 controls the angle of aileron 2 to become by rotating
Change, to adapt to different flying conditions, improve flight efficiency.
Embodiment 3,
Referring to Fig. 1, Fig. 2, Fig. 3 and Fig. 4, there is provided a kind of high stability six rotorcraft, including：The center of regular hexagon
Plate 1, the central plate 1 include upper central plate 101 and lower central plate 102, are provided with six ailerons 2 and are connected by aileron mobile jib 201
The position at six angles of regular hexagon between upper central plate 101 and lower central plate 102, aileron mobile jib 201 are that three sections of bendings are tied
Structure, the end of aileron 2 are furnished with propeller 202, and aileron mobile jib 201 connects the bar segment of propeller 202 higher than in the connection of aileron mobile jib 201
The bar segment of core 1 so that aircraft entirety center of gravity declines, and improves flight stability, propeller 202 is caused after rotation
Promoting air-flow, now, the lift of aircraft, so as to save the efficiency of motor, improves simultaneously to inner side to the outside of central plate 1
The time of flight；
Aileron 2 is connected to the central plate 1 of regular hexagon, the angle between aileron 2 and central plate 1 by aileron connector 203
Degree change is controlled by angle control assembly 3, and aileron connector 203 includes two parallel fixed seats 204, passes through fixed seat 204
It is connected between central plate 101 and lower central plate 102, passes through a connecting rod in the lower rear side of two parallel fixed seats 204
205 connect two fixed seats 204, and the angle control assembly 3 includes motor 301, first gear 302 and second gear
303, second gear 302 is rotatably mounted in the connecting rod 205, and motor 301 drives first gear 302 to rotate,
First gear 302 drives second gear 303 to rotate, and second gear 303 controls the angle change of aileron 2 by rotating, to adapt to
Different flying conditions, improve flight efficiency.
For fit angle control assembly 3, connection otic placode 206 is set in the outer side-lower of two fixed seats 204 of aircraft,
The aircraft also includes the aileron mobile jib connecting seat 207 for being fixedly connected with aileron mobile jib 201, and aileron mobile jib connecting seat 207 is set
For cylindrical structure, the lower section both sides of cylinder have the connection otic placode 208 of triangle, the connection otic placode 208 and fixed seat of triangle
Connection otic placode 206 connected by a spiral shell axle 209 after, connecting seat and fixed seat axis connection are formed, in aileron mobile jib connecting seat 207
The semicircle docking gear 210 of end fixed setting, docking gear 210 are bonded with the second gear 303,303 turns of second gear
It is dynamic to drive docking gear 210 to rotate, so as to drive the angle of aileron mobile jib 201 and the central plate 1 to change.Angle controls
Component 3 controls the axis of aileron mobile jib 201 and the angle of the place plane of central plate 1 to change in the range of ± 5 °.
Fixed seat 204 is by screw connection between upper central plate 101 and lower central plate 102.Motor 301 and first
Gear 302 is arranged on the lower central plate 102.
Aileron 2 connects propeller 202 by aileron mobile jib 201, and motor connection set 211 is connected on the aileron mobile jib 201,
Motor connection set 211 is nested into the end of aileron mobile jib 201, motor connection set 211 and the bolt connection of motor base 212, motor
Machine governor is set in base 212, motor is fixed in motor base 212 and then is tightly connected by motor fixed cover 213, electricity
Fixed cover 214 is set in machine fixed cover 213, propeller 202 is screwed in motor fixed cover 213, and in propeller
Stop washer 215 and locked spacer 216 be set from lower to upper between 202 and fixed cover 213, and lid 217 leads to propeller on motor
Hex(agonal)screw is crossed to be fixedly connected.In flight course, vibration caused by propeller passes through stop washer 215 and locked spacer 216
Offset, prevent it from passing to aircraft body by aileron mobile jib 201, so as to improve the flight stability of aircraft, make to take photo by plane
Picture becomes apparent from.
Embodiment 4,
Referring to Fig. 1, Fig. 2, Fig. 3 and Fig. 4, there is provided a kind of high stability six rotorcraft, including：The center of regular hexagon
Plate 1, the central plate 1 include upper central plate 101 and lower central plate 102, are provided with six ailerons 2 and are connected by aileron mobile jib 201
The position at six angles of regular hexagon between upper central plate 101 and lower central plate 102, aileron mobile jib 201 are that three sections of bendings are tied
Structure, the end of aileron 2 are furnished with propeller 202, and aileron mobile jib 201 connects the bar segment of propeller 202 higher than in the connection of aileron mobile jib 201
The bar segment of core 1 so that aircraft entirety center of gravity declines, and improves flight stability, propeller 202 is caused after rotation
Promoting air-flow, now, the lift of aircraft, so as to save the efficiency of motor, improves simultaneously to inner side to the outside of central plate 1
The time of flight；
Aileron 2 is connected to the central plate 1 of regular hexagon, the angle between aileron 2 and central plate 1 by aileron connector 203
Degree change is controlled by angle control assembly 3, and aileron connector 203 includes two parallel fixed seats 204, passes through fixed seat 204
It is connected between central plate 101 and lower central plate 102, passes through a connecting rod in the lower rear side of two parallel fixed seats 204
205 connect two fixed seats 204, and the angle control assembly 3 includes motor 301, first gear 302 and second gear
303, second gear 302 is rotatably mounted in the connecting rod 205, and motor 301 drives first gear 302 to rotate,
First gear 302 drives second gear 303 to rotate, and second gear 303 controls the angle change of aileron 2 by rotating, to adapt to
Different flying conditions, improve flight efficiency.
For fit angle control assembly 3, connection otic placode 206 is set in the outer side-lower of two fixed seats 204 of aircraft,
The aircraft also includes the aileron mobile jib connecting seat 207 for being fixedly connected with aileron mobile jib 201, and aileron mobile jib connecting seat 207 is set
For cylindrical structure, the lower section both sides of cylinder have the connection otic placode 208 of triangle, the connection otic placode 208 and fixed seat of triangle
Connection otic placode 206 connected by a spiral shell axle 209 after, connecting seat and fixed seat axis connection are formed, in aileron mobile jib connecting seat 207
The semicircle docking gear 210 of end fixed setting, docking gear 210 are bonded with the second gear 303,303 turns of second gear
It is dynamic to drive docking gear 210 to rotate, so as to drive the angle of aileron mobile jib 201 and the central plate 1 to change.Angle controls
Component 3 controls the axis of aileron mobile jib 201 and the angle of the place plane of central plate 1 to change in the range of ± 5 °.
Aileron 2 connects propeller 202 by aileron mobile jib 201, and motor connection set 211 is connected on the aileron mobile jib 201,
Motor connection set 211 is nested into the end of aileron mobile jib 201, motor connection set 211 and the bolt connection of motor base 212, motor
Machine governor is set in base 212, motor is fixed in motor base 212 and then is tightly connected by motor fixed cover 213, electricity
Fixed cover 214 is set in machine fixed cover 213, propeller 202 is screwed in motor fixed cover 213, and in propeller
Stop washer 215 and locked spacer 216 be set from lower to upper between 202 and fixed cover 213, and lid 217 leads to propeller on motor
Hex(agonal)screw is crossed to be fixedly connected.In flight course, vibration caused by propeller passes through stop washer 215 and locked spacer 216
Offset, prevent it from passing to aircraft body by aileron mobile jib 201, so as to improve the flight stability of aircraft, make to take photo by plane
Picture becomes apparent from.
During aircraft flight, wind-force is that an important factor for influenceing aircraft flight stability, having wind weather not
Without take photo by plane monitoring etc. task when, be typically due to the influence of windage, the stability of aircraft can all substantially reduce, therefore be
Reduction windage, on the basis of above example, regular hexagon between central plate 101 and lower central plate 102 on board the aircraft
The position on six sides sets the central plate closing cap 103 that vertical section is arc.Because the vertical section of closing cap 103 is arc, i.e.,
It is streamlined, so as on the one hand prevent wind from entering aircraft body, on the other hand reduce windage, it is steady to greatly improve aircraft flight
It is qualitative.
Embodiment 5,
Referring to Fig. 1, Fig. 2, Fig. 3 and Fig. 4, there is provided a kind of high stability six rotorcraft, including：The center of regular hexagon
Plate 1, the central plate 1 include upper central plate 101 and lower central plate 102, are provided with six ailerons 2 and are connected by aileron mobile jib 201
The position at six angles of regular hexagon between upper central plate 101 and lower central plate 102, aileron mobile jib 201 are that three sections of bendings are tied
Structure, the end of aileron 2 are furnished with propeller 202, and aileron mobile jib 201 connects the bar segment of propeller 202 higher than in the connection of aileron mobile jib 201
The bar segment of core 1 so that aircraft entirety center of gravity declines, and improves flight stability, propeller 202 is caused after rotation
Promoting air-flow, now, the lift of aircraft, so as to save the efficiency of motor, improves simultaneously to inner side to the outside of central plate 1
The time of flight；
Aileron 2 is connected to the central plate 1 of regular hexagon, the angle between aileron 2 and central plate 1 by aileron connector 203
Degree change is controlled by angle control assembly 3, and aileron connector 203 includes two parallel fixed seats 204, passes through fixed seat 204
It is connected between central plate 101 and lower central plate 102, passes through a connecting rod in the lower rear side of two parallel fixed seats 204
205 connect two fixed seats 204, and the angle control assembly 3 includes motor 301, first gear 302 and second gear
303, second gear 302 is rotatably mounted in the connecting rod 205, and motor 301 drives first gear 302 to rotate,
First gear 302 drives second gear 303 to rotate, and second gear 303 controls the angle change of aileron 2 by rotating, to adapt to
Different flying conditions, improve flight efficiency.
For fit angle control assembly 3, connection otic placode 206 is set in the outer side-lower of two fixed seats 204 of aircraft,
The aircraft also includes the aileron mobile jib connecting seat 207 for being fixedly connected with aileron mobile jib 201, and aileron mobile jib connecting seat 207 is set
For cylindrical structure, the lower section both sides of cylinder have the connection otic placode 208 of triangle, the connection otic placode 208 and fixed seat of triangle
Connection otic placode 206 connected by a spiral shell axle 209 after, connecting seat and fixed seat axis connection are formed, in aileron mobile jib connecting seat 207
The semicircle docking gear 210 of end fixed setting, docking gear 210 are bonded with the second gear 303,303 turns of second gear
It is dynamic to drive docking gear 210 to rotate, so as to drive the angle of aileron mobile jib 201 and the central plate 1 to change.Angle controls
Component 3 controls the axis of aileron mobile jib 201 and the angle of the place plane of central plate 1 to change in the range of ± 5 °.
Aileron 2 connects propeller 202 by aileron mobile jib 201, and motor connection set 211 is connected on the aileron mobile jib 201,
Motor connection set 211 is nested into the end of aileron mobile jib 201, motor connection set 211 and the bolt connection of motor base 212, motor
Machine governor is set in base 212, motor is fixed in motor base 212 and then is tightly connected by motor fixed cover 213, electricity
Fixed cover 214 is set in machine fixed cover 213, propeller 202 is screwed in motor fixed cover 213, and in propeller
Stop washer 215 and locked spacer 216 be set from lower to upper between 202 and fixed cover 213, and lid 217 leads to propeller on motor
Hex(agonal)screw is crossed to be fixedly connected.In flight course, vibration caused by propeller passes through stop washer 215 and locked spacer 216
Offset, prevent it from passing to aircraft body by aileron mobile jib 201, so as to improve the flight stability of aircraft, make to take photo by plane
Picture becomes apparent from.
During aircraft flight, wind-force is that an important factor for influenceing aircraft flight stability, having wind weather not
Without take photo by plane monitoring etc. task when, be typically due to the influence of windage, the stability of aircraft can all substantially reduce, therefore be
Reduction windage, on the basis of above example, regular hexagon between central plate 101 and lower central plate 102 on board the aircraft
The position on six sides sets the central plate closing cap 103 that vertical section is arc.Because the vertical section of closing cap 103 is arc, i.e.,
It is streamlined, so as on the one hand prevent wind from entering aircraft body, on the other hand reduce windage, it is steady to greatly improve aircraft flight
It is qualitative.
In order to be taken photo by plane using the aircraft, gondola 401 is additionally provided with below high stability six rotorcraft.Gondola
401 are connected by gondola connecting rod 402 with aircraft.And two supports 501, energy are set below high stability six rotorcraft
Enough aircraft is set stably to land.
Claims (11)
1. a kind of high stability six rotorcraft, it is characterised in that the aircraft includes：The central plate of regular hexagon, in this
Core includes upper central plate and lower central plate, is provided with six ailerons and is connected to upper central plate and lower central plate by aileron mobile jib
Between regular hexagon six angles position, aileron mobile jib is three sections of bending structures, and aileron end is furnished with propeller, aileron mobile jib
Connect propeller bar segment be higher than aileron mobile jib connecting central plate bar segment, propeller after rotation, it is caused promotion air-flow to
On the outside of central plate；
The aileron is connected to the central plate of regular hexagon by aileron connector, the angle change between aileron and central plate by
Angle control assembly is controlled, and aileron connector includes two parallel fixed seats, and upper central plate is connected to under by fixed seat
Between central plate, two fixed seats are connected by a connecting rod in the lower rear side of two parallel fixed seats, the angle control
Component processed includes motor, first gear and second gear, and second gear is rotatably mounted in the connecting rod, driving
Motor drives first gear to rotate, and first gear drives second gear to rotate, and second gear controls the angle of aileron by rotating
Change.
2. high stability six rotorcraft as claimed in claim 1, it is characterised in that in the outer side-lower of two fixed seats
Connection otic placode is set, and the aircraft also includes the aileron mobile jib connecting seat for being fixedly connected with aileron mobile jib, aileron mobile jib connecting seat
It is arranged to cylindrical structure, the lower section both sides of cylinder have a connection otic placode of triangle, the connection otic placode of triangle and fixed seat
After connection otic placode is by a spiral shell axis connection, connecting seat and fixed seat axis connection are formed, fixes and sets in aileron mobile jib connecting seat end
Semicircle docking gear is put, docking gear is bonded with the second gear, and second gear, which rotates, drives opposing teeth wheel to rotate, so as to
The angle of aileron mobile jib and the central plate is driven to change.
3. the high stability six rotorcraft as described in claim 1 or 2 is any, it is characterised in that the angle control group
Part controls the aileron mobile jib axis and the angle of plane where the central plate to change in the range of ± 5 °.
4. the high stability six rotorcraft as described in claim 1 or 2 is any, it is characterised in that the fixed seat passes through
Screw connection is between upper central plate and lower central plate.
5. the high stability six rotorcraft as described in claim 1 or 2 is any, it is characterised in that the motor and
First gear is arranged on the lower central plate.
6. high stability six rotorcraft as claimed in claim 1, it is characterised in that the aileron is connected by aileron mobile jib
Propeller is connect, connects motor connection set on the aileron mobile jib, motor connection set is nested into the end of aileron mobile jib, motor connection
Set and motor base bolt connection, machine governor is set in motor base, and motor is fixed in motor base and then passes through motor
Fixed cover is tightly connected, and fixed cover is set in motor fixed cover, and propeller is screwed in motor fixed cover, and in spiral shell
Stop washer and locked spacer are set from lower to upper between rotation oar and fixed cover, covers on motor and is consolidated with propeller by hex(agonal)screw
Fixed connection.
7. high stability six rotorcraft as claimed in claim 1, it is characterised in that the upper central plate and lower central plate
Between six sides of regular hexagon position set central plate closing cap.
8. high stability six rotorcraft as claimed in claim 7, it is characterised in that the central plate closing cap vertical section
For arc.
9. high stability six rotorcraft as claimed in claim 1, it is characterised in that the rotor flying of high stability six
Gondola is additionally provided with below device.
10. high stability six rotorcraft as claimed in claim 9, it is characterised in that the gondola is connected by gondola
Bar is connected with aircraft.
11. high stability six rotorcraft as claimed in claim 1, it is characterised in that the rotor of high stability six flies
Two supports are set below row device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720371848.4U CN206782062U (en) | 2017-04-11 | 2017-04-11 | A kind of high stability six rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720371848.4U CN206782062U (en) | 2017-04-11 | 2017-04-11 | A kind of high stability six rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206782062U true CN206782062U (en) | 2017-12-22 |
Family
ID=60706089
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720371848.4U Active CN206782062U (en) | 2017-04-11 | 2017-04-11 | A kind of high stability six rotorcraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206782062U (en) |
-
2017
- 2017-04-11 CN CN201720371848.4U patent/CN206782062U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205707301U (en) | A kind of pulp distance varying mechanism | |
| US9889925B2 (en) | Single blade propeller with variable pitch | |
| CN104743107B (en) | Multi-rotor aerocraft | |
| CN101175918A (en) | Vertical axis wind turbines | |
| CN203996886U (en) | A kind of four axle eight oars aircraft of taking photo by plane | |
| CN103661927A (en) | Variable pitch propeller of fixed-wing aircraft | |
| CN107244415A (en) | The composite power rotor wing unmanned aerial vehicle that a kind of fuselage can vert | |
| CN109733603A (en) | A kind of boxlike solar energy unmanned plane | |
| CN206968964U (en) | A kind of unmanned airplane empennage rudder face directly drives control device | |
| CN101177167A (en) | Power-driven system of aircraft | |
| CN106741904A (en) | A kind of compound unmanned vehicle | |
| CN106904270A (en) | A kind of high stability six rotorcraft | |
| CN107161330A (en) | A kind of variable abnormally-structured displacement multi-rotor unmanned aerial vehicle | |
| CN109153449A (en) | Propeller, Power Component and unmanned vehicle | |
| CN108639311B (en) | Stop device of full-electric vertical take-off and landing fixed wing unmanned aerial vehicle front flying propeller | |
| CN207631487U (en) | Propeller, Power Component and unmanned vehicle | |
| CN103991540A (en) | Conical rotary flapping wing aircraft | |
| CN206782062U (en) | A kind of high stability six rotorcraft | |
| CN106114842A (en) | A kind of oil electricity mixing coaxial dual-rotor helicopter and using method thereof | |
| CN207089645U (en) | A kind of energy-efficient electric power drives six rotor wing unmanned aerial vehicles | |
| CN106965921A (en) | Fixed-wing and the integral unmanned aerial vehicle of many rotors | |
| CN208393624U (en) | A kind of coaxial anti-paddle rotor system of culvert type | |
| CN208310906U (en) | Aircraft and its air throttle | |
| CN109250095A (en) | A kind of VTOL fixed wing aircraft | |
| CN210083537U (en) | High stability I-shaped unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |