CN107685872A - Unmanned vehicle - Google Patents
Unmanned vehicle Download PDFInfo
- Publication number
- CN107685872A CN107685872A CN201710945255.9A CN201710945255A CN107685872A CN 107685872 A CN107685872 A CN 107685872A CN 201710945255 A CN201710945255 A CN 201710945255A CN 107685872 A CN107685872 A CN 107685872A
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- Prior art keywords
- unmanned vehicle
- horn
- fuselage
- component
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- 230000000712 assembly Effects 0.000 claims abstract description 15
- 238000000429 assembly Methods 0.000 claims abstract description 15
- 230000003416 augmentation Effects 0.000 claims description 4
- 230000005611 electricity Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims description 2
- 230000001154 acute effect Effects 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 230000000007 visual effect Effects 0.000 abstract description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 206010044565 Tremor Diseases 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 210000003127 knee Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
- B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Accessories Of Cameras (AREA)
Abstract
The present invention relates to aircraft field, there is provided a kind of unmanned vehicle, including fuselage, horn component, Power Component and camera assembly.The horn component is installed on the fuselage；The Power Component is installed on the horn component, for providing flying power for the unmanned vehicle；At least four camera assemblies are respectively arranged in the horn component, and the opposite sides of the fuselage respectively sets at least two camera assemblies.During the unmanned vehicle flight of the present invention, at least four camera assemblies positioned at the opposite sides of the fuselage can complete 360 degree of pan-shot jointly, ensure to get 360 degree of full-view image within the same time, and then the 3-dimensional stereoscopic experience sense in virtual reality can be met.At least four camera assemblies are installed on the horn component, and its visual angle is open, will not be blocked by the fuselage or other carrying equipments, and can realize no dead angle pan-shot.
Description
【Technical field】
The present invention relates to aircraft field, more particularly to a kind of unmanned vehicle with shoot function.
【Background technology】
UAV, abbreviation unmanned vehicle (UAV), it is a kind of new ideas equipment being in developing rapidly, its
The advantages of low is required with maneuverability, rapid reaction, unmanned, operation.Unmanned vehicle is by carrying multiclass sensor
Or picture pick-up device, it is possible to achieve image real-time Transmission, high-risk areas detecting function be satellite remote sensing to be had with traditional air remote sensing
Power is supplemented.
In current unmanned vehicle, the conventional camera assembly visual angle for realizing pan-shot is narrower, easily by fuselage
Or other carrying equipments block, it is impossible to fully meet use demand.
【The content of the invention】
In order to solve the above-mentioned technical problem, the embodiment of the present invention provides a kind of achievable pan-shot and shooting visual angle is opened
Wealthy unmanned vehicle.
The embodiment of the present invention solves its technical problem and uses following technical scheme：
A kind of unmanned vehicle, including fuselage, horn component, Power Component and camera assembly.The horn component peace
Loaded on the fuselage；The Power Component is installed on the horn component, for providing flying power for the unmanned vehicle；
At least four camera assemblies are respectively arranged in the horn component, and the opposite sides of the fuselage respectively sets at least two institutes
State camera assembly.
Alternatively, each camera assembly includes camera device, and the camera device includes at least one camera lens.
Alternatively, each camera assembly includes head, and the head is installed on the horn component, the shooting dress
Put and be installed on the head.
Alternatively, the head is three-axis stability augmentation head, including the first motor, the second motor and the 3rd motor；
The stator of 3rd motor is installed on the horn component, rotor connection second electricity of the 3rd motor
The stator of machine, and the rotor of second motor connects the stator of first motor, the camera device are installed on described the
The rotor of one motor.
Alternatively, the horn component includes drive component and horn；
One end of two horns is hinged, and two horns are located at the opposite sides of the fuselage respectively；
The drive component is installed on the fuselage, and the drive component is connected with two horns, for driving
Move two horns so that angle increase or reduction between two horns.
Alternatively, the drive component includes：Drive device, movable part and actuator；
The drive device is fixedly installed in the fuselage, for driving the movable part to do linear reciprocating motion；
The quantity of the actuator is two, and one end of one of them actuator is hinged one end of the movable part,
One end of another actuator is hinged the other end of the movable part, each actuator away from the movable part one
End is hinged a corresponding horn.
Alternatively, the drive component includes screw rod；
The drive device is connected with the screw rod, for driving the screw rod to rotate；
The movable part is sheathed on the screw rod, and can be done with the rotation of the screw rod along the axis of the screw rod past
Linear motion.
Alternatively, each actuator includes body, first connecting portion and second connecting portion；
Two first connecting portions are extended from the side of the body, the end of two first connecting portions
It is arranged at intervals, the end of two first connecting portions is hinged a corresponding horn；
Two second connecting portions are extended from the opposite side of the body, the end of two second connecting portions
End is arranged at intervals, and the end of two second connecting portions is located at the both sides of the movable part, and with one end of the movable part
It is be hinged.
Alternatively, each horn includes arm body and mounting seat；
The mounting seat is fixed in one end of the arm body；
Two mounting seats are hinged, and each be hinged one of the one end of the actuator away from the movable part is corresponding
The mounting seat.
Alternatively, the mounting seat includes tube body and articulated section；
One end of the arm body is inserted and fixed in the tube body；
Two articulated sections are extended from one end of the tube body, and the space from end of two articulated sections is set
Put, the end of the end of two articulated sections of one of them mounting seat and two articulated sections of another mounting seat is handed over
For overlapping, and the end of the articulated section of two mounting seats is hinged.
Alternatively, the horn component includes installing arm, the middle part machine corresponding with one of each installing arm
One end connection of the arm away from the fuselage；
Camera assembly described in each two is respectively arranged in the opposite end of a corresponding installing arm.
Alternatively, the horn component includes fix bar, and the fix bar includes the body of rod and connector, and the one of the body of rod
End is hinged the fuselage, and the other end of the body of rod is hinged one end of the connector, the other end be hinged one of the connector
The individual corresponding installing arm.
Alternatively, above-mentioned unmanned vehicle includes landing gear assembly, and the landing gear assembly includes land bar and support bar；
One end of the land bar is fixedly installed in the installing arm, in sharp between the land bar and the installing arm
Angle；
One end of the support bar is fixedly installed in the installing arm, and the other end of the support bar is fixedly installed in described
Land bar, and it is separated by default distance with the end of the land bar.
Compared with prior art, in the unmanned vehicle flight of the embodiment of the present invention, positioned at the relative of the fuselage
At least four camera assemblies of both sides can complete 360 degree of pan-shot jointly, ensure to get within the same time
360 degree of full-view image, and then the 3-dimensional stereoscopic experience sense in virtual reality can be met.At least four camera assembly installations
In the horn component, its visual angle is open, will not be blocked by the fuselage or other carrying equipments, and can realize no dead angle panorama
Shooting.
【Brief description of the drawings】
One or more embodiments are illustrative by corresponding accompanying drawing, these exemplary illustrations not structure
The restriction of paired embodiment, the element for having same reference numbers label in accompanying drawing is expressed as similar element, unless there are special
Declare, composition does not limit the figure in accompanying drawing.
Fig. 1 is a kind of stereogram for unmanned vehicle that a wherein embodiment of the invention provides；
Fig. 2 is the front view of the unmanned vehicle shown in Fig. 1；
Fig. 3 is stereogram of the fuselage with horn component of the unmanned vehicle shown in Fig. 1, wherein a part for the fuselage
It is omitted；
Fig. 4 is the side view of the fuselage shown in Fig. 3 and horn component；
Fig. 5 is along the sectional view of line A-A in Fig. 4；
Fig. 6 is the exploded view of the fuselage shown in Fig. 3 and horn component.
【Embodiment】
For the ease of understanding the present invention, below in conjunction with the accompanying drawings and specific embodiment, the present invention will be described in more detail.
It should be noted that when element is expressed " being fixed on " another element, it can directly on another element or therebetween
There may be one or more elements placed in the middle.When an element is expressed " connection " another element, it can directly be connected
It is connected to another element or there may be one or more elements placed in the middle therebetween.Term used in this specification is " vertical
", " horizontal ", "left", "right", " interior ", " outer " and similar statement for illustrative purposes only.
Unless otherwise defined, technology all used in this specification and scientific terminology are led with belonging to the technology of the present invention
The implication that the technical staff in domain is generally understood that is identical.It is specific to be intended merely to description for used term in the description of the invention
Embodiment purpose, be not intended to limitation the present invention.Term "and/or" used in this specification includes one or more phases
The arbitrary and all combination of the Listed Items of pass.
In addition, as long as technical characteristic involved in invention described below difference embodiment is not formed each other
Conflict can be combined with each other.
Fig. 1 and Fig. 2, a kind of unmanned vehicle 100 that a wherein embodiment of the invention provides, including fuselage 10 are referred to,
Horn component 20, Power Component 30, camera assembly 40 and landing gear assembly 50.The horn component 20 is installed on the fuselage
10, the Power Component 30 is installed on the horn component 20, for for the unmanned vehicle 100 provide flying power, four
The individual camera assembly 40 is respectively arranged in the horn component 20, and camera assembly 40 described in each two is located at the fuselage
10 opposite sides, the landing gear assembly 50 are installed on the horn component 20.
Include the control circuit component being made up of electronic components such as MCU, the control circuit component bag in the fuselage 10
Include multiple control modules, e.g., for the control module for controlling the horn component 20 to pack up or put down, for control it is described nobody
The flight control modules of the flight attitude of aircraft 100, the locating module for the unmanned vehicle 100 that navigates and it is used for
Handle data processing module of the environmental information acquired in related airborne equipment etc..
Also referring to Fig. 3 to Fig. 5, the fuselage 10 opens up accepting groove 102, for horn component described in partial receipt
20。
The horn component 20 includes drive component 210, horn 220, fix bar 230 and installing arm 240.The driving group
Part 210 is arranged in the accepting groove 102 of the fuselage 10, and the drive component 210 is connected with the horn 220, to institute
State horn 220 and power is provided, drive the horn 220 to pack up or put down.The horn 220 is connected with the installing arm 240, institute
Installing arm 240 is stated to be used to the Power Component 30, the camera assembly 40 and the landing gear assembly 50 are installed.The fixation
The both ends of bar 230 are respectively articulated with the fuselage 10 and the installing arm 240, for applying to the horn 220 and installing arm 240
Towards the pulling force of the fuselage 10 so that the horn 220 stably can be packed up or put down, and reduce trembling in moving process
It is dynamic.
The drive component 210 is installed on the fuselage 10.The drive component 210 includes：Drive device 212, screw rod
214, movable part 216 and actuator 218.The drive device 212 is fixedly installed in the fuselage 10, itself and the screw rod
214 connections, for driving the screw rod 214 to rotate.Described one end of screw rod 214 is fixedly connected with the rotating shaft of the drive device 212,
The other end is rotationally connected with the fuselage 10.The movable part 216 is sheathed on the screw rod 214, and can be with the screw rod 214
Rotation, do linear reciprocating motion along the axis of the screw rod 214.The quantity of the actuator 218 is two, one of institute
The one end for stating actuator 218 is hinged one end of the movable part 216, and one end of another actuator 218 is hinged the work
The other end of moving part 216.
In the present embodiment, the drive device 212 includes a motor, for driving the screw rod 214 to rotate, and then makes
The movable part 216 is obtained with the rotation of the screw rod 214, linear reciprocating motion is done along the axis of the screw rod 214.
It is understood that in some other embodiments, the screw rod 214 can omit, and the drive device 212 can
To be one kind in cylinder or hydraulic cylinder, the drive device 212 is connected with the movable part 216, for driving the activity
Part 216 does linear reciprocating motion.
The quantity of the horn 220 is two, is in angle between two horns 220, two horns 220 are distinguished
Positioned at the opposite sides of the fuselage 10.Each horn 220 includes arm body 222 and mounting seat 224, the arm body 222
One end is inserted and fixed in the mounting seat 224.Two mounting seats 224 are hinged, and each actuator 218 is remote
One end of the movable part 216 is hinged a corresponding mounting seat 224.When the drive device 212 works, the drive
Dynamic device 212 drives the screw rod 214 to rotate, and drives axis of the movable part 216 along the screw rod 214 to do reciprocating linear fortune
Dynamic, under the drive of the movable part 216, the actuator 218 drives two horns 220 to pack up or put down.
Referring to Fig. 6, each actuator 218 includes body 2180, first connecting portion 2182 and second connecting portion
2184.The first connecting portion 2182 is shaft-like, and two first connecting portions 2182 are prolonged from the side of the body 2180
Stretch, the space from end of two first connecting portions 2182 is set.Similarly, the second connecting portion 2184 is also bar
Shape, two second connecting portions 2184 are extended from the opposite side of the body 2180, two second connecting portions
2184 space from end is set.The end of two second connecting portions 2184 is located at the both sides of the movable part 216, and with institute
The one end for stating movable part 216 is hinged.
The mounting seat 224 includes tube body 2242, bearing pin 2244 and articulated section 2246.The tube body 2242 opens up
There is mounting hole (not shown), one end of the arm body 222 is inserted and fixed in the mounting hole.The quantity of the bearing pin 2244 is
Two, two bearing pins 2244 are fixedly installed in the opposite sides of the tube body 2242 respectively, each bearing pin 2244
The end of the first connecting portion 2182 corresponding with one is hinged so that the actuator 218 is articulated with the mounting seat
224.The 2246 have a generally triangular shape tabular of articulated section, quantity are two, and two articulated sections 2246 are from the tube body
2242 one end is extended, and the space from end of two articulated sections 2246 is set.The two of one of them mounting seat 224
The alternately stacked setting in end of the end of individual articulated section 2246 and two articulated sections 2246 of another mounting seat 224, and
And the end of the articulated section 2246 of two mounting seats 224 is hinged.
The fix bar 230 includes the body of rod 232 and connector 234, and one end of the body of rod 232 is hinged the fuselage 10,
The other end of the body of rod 232 is hinged one end of the connector 234, and the other end of the connector 234 is hinged the dress arm
240.When the unmanned vehicle 100 is in state of flight, the Power Component 30 is to the horn 220 away from the fuselage
10 one end and installing arm 240 provide upward pulling force, and the fix bar 230 provides court to the horn 220 and installing arm 240
To the pulling force of the fuselage 10, to prevent the horn 220 from further being rotated relative to the fuselage 10, so that described
Horn 220 is in stable state.
The quantity of the installing arm 240 is two, each installing arm 240 substantially straight-bar, its middle part and the machine
One end connection of the arm 220 away from fuselage 10.Two installing arms 240 are arranged in parallel in relative the two of the fuselage 10
Side.It is understood that in some other embodiments, the shape and set-up mode of the installing arm 240 can be according to reality
Need to change, for example, the installing arm 240 can be knee etc..
Referring back to Fig. 1 and Fig. 2, the Power Component 30 includes motor and is installed on the propeller of the motor, is used for
Flying power is provided for the unmanned vehicle 100.The quantity of the Power Component 30 is four, Power Component described in each two
30 are respectively arranged in the opposite end of the installing arm 240 corresponding to one.
It is understood that in some other embodiments, the quantity of the Power Component 30 can according to circumstances increase or
Reduce, for example, 6,8 etc. are reduced to 1,2 or increase to, for example, when the quantity of the Power Component 30 is two,
The installing arm 240 can be omitted, and each Power Component 30 can be fixedly installed in one of the horn 220 away from fuselage 10
End；For example, when the quantity of the Power Component 30 is 6,8, it can accordingly increase the horn 220 and the number of installing arm 240
Amount.
The quantity of the camera assembly 40 is four, and camera assembly 40 described in each two is removably installed in one accordingly
The installing arm 240 opposite end.
Each camera assembly 40 includes head 44 and camera device 46.
The head 44 is three-axis stability augmentation head, and the three-axis stability augmentation head is on three axles to the shooting in-flight
Device 46 increase surely：Course axle (Yaw), pitch axis (Pitch) and roll axis (Roll).The pitch axis is perpendicular to rolling
Axle, course axle is perpendicular to pitch axis and roll axis.
The head 44 includes：First motor, the second motor and the 3rd motor.The central shaft of the rotor of first motor with
Roll axis is coaxial.The central shaft of the rotor of second motor and pitch axis are coaxial, and the central shaft of the rotor of the 3rd motor and course
Axle is coaxial.The stator of 3rd motor is removably installed in one end of the installing arm 240 by fixed seat, and the 3rd motor turns
The stator of son the second motor of connection, and the rotor of the second motor connects the stator of the first motor.
It is understood that in some other embodiments, the 3rd motor can omit, and the stator of the second motor leads to
Cross one end that fixed seat is removably installed in the installing arm 240.
The head 44 is removably installed in one end of the installing arm 240 by fixed seat, can facilitate the shooting
The replacing of component 40.The head 44 can be removably installed in the one of the installing arm 240 by structures such as buckle, screw threads
End.
The camera device 46 is fixedly installed in the rotor of the first motor of the head 44.The camera device 46 can be with
First-class for camera, video camera, shooting, it can include at least one camera lens, such as each camera device 46 includes two
Backwards to the camera lens of setting.Four camera devices 46 are generally aligned in the same plane, and four camera devices 46 are located at one
Rectangular four angles, it is ensured that without shooting blind angle amount, and stronger relief full-view image can be obtained.
It is understood that the quantity of the camera assembly 40 can be at least four, as long as the fuselage 10 is relative
Both sides respectively set at least two camera assemblies 40 to complete pan-shot, for example, the quantity of the camera assembly 40 is
Six, the opposite sides of the fuselage 10 respectively sets three camera assemblies 40, and two camera assemblies 40 are removably
The opposite end of a corresponding installing arm 240 is installed on, the 3rd camera assembly 40 is removably installed in one
The middle part of the individual corresponding installing arm 240.The camera device 46 of at least four camera assemblies 40 is generally aligned in the same plane, and
And wherein four camera devices 46 are located at rectangular four angle.
It is understood that in some other embodiments, the head 44 or single shaft head；Or the cloud
Platform 44 omits, and the camera device 46 is directly mounted at the installing arm 240.
Referring back to Fig. 3 to Fig. 5, the landing gear assembly 50 includes land bar 502 and support bar 504.The land bar
502 one end is fixedly installed in one end of the installing arm 240, in sharp between the land bar 502 and the installing arm 240
Angle, one end of the support bar 504 are fixedly installed in the installing arm 240, and the other end of the support bar 504 is fixedly installed in
The land bar 502, and it is separated by default distance with the end of the land bar 502.Described in the support bar 504 and part
It is triangle to fall bar 502 and the part installing arm 240, in 100 land of unmanned vehicle, the undercarriage group
Part 50 can consolidate the support unmanned vehicle 100.
It is understood that in some other embodiments, the landing gear assembly 50 may also include drive device, described
Drive device can be cylinder or hydraulic cylinder, and it is installed on the installing arm 240, and one end of the support bar 504 is installed on described
Drive device, the other end are installed on the land bar 502, and one end of the land bar 502 is articulated with the installing arm 240.Make
Used time, the drive device can drive the support bar 504 for linear motion along the axis of its drive rod, described so as to drive
Fall bar 502 to rotate relative to the installing arm 240 so that the land bar 502 can be laid down or pack up.
In 100 flight of unmanned vehicle, positioned at four camera assemblies of the opposite sides of the fuselage 10
40 can complete 360 degree of pan-shot jointly, ensure to get 360 degree of full-view image within the same time, and then can be full
3-dimensional stereoscopic experience sense in sufficient virtual reality.Because four camera assemblies 40 are installed on the horn component 20 so that its
Visual angle is open, will not be blocked by the fuselage 10 or other carrying equipments, and can realize no dead angle pan-shot.
In addition, camera assembly 40 described in each two is installed on the opposite end of a corresponding installing arm 240, four
The camera assembly 40 is generally aligned in the same plane, and four camera assemblies 40 are located at rectangular four angle, can obtain
Obtain stronger relief full-view image.
Moreover, the drive component 210 can drive two horns 220 so that the folder between two horns 220
Angle increases or reduced, so as to can adjust the spacing between the camera assembly 40 of the opposite sides of the fuselage 10, with
Adapt to different photographing requests.
Finally it should be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；At this
Under the thinking of invention, it can also be combined between the technical characteristic in above example or different embodiments, step can be with
Realized with random order, and many other changes of the different aspect of the present invention as described above be present, for simplicity, they do not have
Have and provided in details；Although the present invention is described in detail with reference to the foregoing embodiments, the ordinary skill people of this area
Member should be understood：It can still modify to the technical scheme described in foregoing embodiments, or to which part skill
Art feature carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from each reality of the present invention
Apply the scope of a technical scheme.
Claims (13)
- A kind of 1. unmanned vehicle (100), it is characterised in that including：Fuselage (10)；Horn component (20), the horn component (20) are installed on the fuselage (10)；Power Component (30), the Power Component (30) are installed on the horn component (20), for for the unmanned vehicle (100) flying power is provided；Camera assembly (40), at least four camera assemblies (40) are respectively arranged in the horn component (20), the fuselage (10) opposite sides respectively sets at least two camera assemblies (40).
- 2. unmanned vehicle (100) according to claim 1, it is characterised in that each camera assembly (40) includes Camera device (46), the camera device (46) include at least one camera lens.
- 3. unmanned vehicle (100) according to claim 2, it is characterised in that each camera assembly (40) includes Head (44), the head (44) are installed on the horn component (20), and the camera device (46) is installed on the head (44)。
- 4. unmanned vehicle (100) according to claim 3, it is characterised in that the head (44) is three-axis stability augmentation cloud Platform, including the first motor, the second motor and the 3rd motor；The stator of 3rd motor is installed on the horn component (20), rotor connection second electricity of the 3rd motor The stator of machine, and the rotor of second motor connects the stator of first motor, the camera device (46) is installed on institute State the rotor of the first motor.
- 5. the unmanned vehicle (100) according to any one of Claims 1-4, it is characterised in that the horn component (20) Including drive component (210) and horn (220)；One end of two horns (220) is hinged, and two horns (220) are located at the phase of the fuselage (10) respectively To both sides；The drive component (210) is installed on the fuselage (10), and the drive component (210) and two horns (220) connect, for driving two horns (220) so that the angle between two horns (220) increases or subtracted It is small.
- 6. unmanned vehicle (100) according to claim 5, it is characterised in that the drive component (210) includes：Drive Dynamic device (212), movable part (216) and actuator (218)；The drive device (212) is fixedly installed in the fuselage (10), for driving the movable part (216) to do reciprocating linear Motion；The quantity of the actuator (218) is two, and one end of one of them actuator (218) is hinged the movable part (216) one end, one end of another actuator (218) are hinged the other end of the movable part (216), each drive The one end of moving part (218) away from the movable part (216) is hinged a corresponding horn (220).
- 7. unmanned vehicle (100) according to claim 6, it is characterised in that the drive component (210) includes screw rod (214)；The drive device (212) is connected with the screw rod (214), for driving the screw rod (214) to rotate；The movable part (216) is sheathed on the screw rod (214), and can be with the rotation of the screw rod (214), along the screw rod (214) axis does linear reciprocating motion.
- 8. the unmanned vehicle (100) according to claim 6 or 7, it is characterised in that each actuator (218) bag Include body (2180), first connecting portion (2182) and second connecting portion (2184)；Two first connecting portions (2182) are extended from the side of the body (2180), two first connections The space from end in portion (2182) is set, and the end of two first connecting portions (2182) is hinged a corresponding horn (220)；Two second connecting portions (2184) are extended from the opposite side of the body (2180), and two described second connect The space from end of socket part (2184) is set, and the end of two second connecting portions (2184) is located at the movable part (216) Both sides, and be hinged with one end of the movable part (216).
- 9. unmanned vehicle (100) according to claim 8, it is characterised in that each horn (220) includes arm body And mounting seat (224) (222)；The mounting seat (224) is fixed in one end of the arm body (222)；Two mounting seats (224) are hinged, each one end of the actuator (218) away from the movable part (216) It is hinged a corresponding mounting seat (224).
- 10. unmanned vehicle (100) according to claim 9, it is characterised in that the mounting seat (224) includes body Portion (2242) and articulated section (2246)；One end of the arm body (222) is inserted and fixed in the tube body (2242)；Two articulated sections (2246) are extended from one end of the tube body (2242), two articulated sections (2246) Space from end set, the ends of two articulated sections (2246) of one of them mounting seat (224) and another described peace Fill the alternately stacked setting in end of two articulated sections (2246) of seat (224), and the hinge of two mounting seats (224) The end of socket part (2246) is hinged.
- 11. the unmanned vehicle (100) according to claim any one of 5-10, it is characterised in that the horn component (20) installing arm (240) is included, the middle part horn (220) corresponding with one of each installing arm (240) is away from institute State one end connection of fuselage (10)；Camera assembly described in each two (40) is respectively arranged in the opposite end of a corresponding installing arm (240).
- 12. unmanned vehicle (100) according to claim 11, it is characterised in that the horn component (20) includes solid Fixed pole (230), the fix bar (230) include the body of rod (232) and connector (234), and one end of the body of rod (232) is hinged institute State fuselage (10), the other end of the body of rod (232) is hinged one end of the connector (234), the connector (234) it is another One end is hinged a corresponding installing arm (240).
- 13. the unmanned vehicle (100) according to claim 11 or 12, it is characterised in that including landing gear assembly (50), The landing gear assembly (50) includes land bar (502) and support bar (504)；One end of the land bar (502) is fixedly installed in the installing arm (240), the land bar (502) and the installation It is at an acute angle between arm (240)；One end of the support bar (504) is fixedly installed in the installing arm (240), and the other end of the support bar (504) is consolidated Dingan County is loaded on the land bar (502), and is separated by default distance with the end of the land bar (502).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710945255.9A CN107685872A (en) | 2017-09-30 | 2017-09-30 | Unmanned vehicle |
| PCT/CN2018/086730 WO2019062140A1 (en) | 2017-09-30 | 2018-05-14 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
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| CN201710945255.9A CN107685872A (en) | 2017-09-30 | 2017-09-30 | Unmanned vehicle |
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| CN107685872A true CN107685872A (en) | 2018-02-13 |
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| CN201710945255.9A Pending CN107685872A (en) | 2017-09-30 | 2017-09-30 | Unmanned vehicle |
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| WO (1) | WO2019062140A1 (en) |
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| CN108482649A (en) * | 2018-03-01 | 2018-09-04 | 昆明创培知识产权服务有限公司 | A kind of more rotary wind type unmanned plane magnetic levitation vibration damping devices |
| WO2019062140A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN113335496A (en) * | 2021-06-19 | 2021-09-03 | 国网浙江省电力有限公司浦江县供电公司 | Be applied to unmanned aerial vehicle horn subassembly that electric power cruises |
| WO2022052645A1 (en) * | 2020-09-11 | 2022-03-17 | 广州极飞科技股份有限公司 | Unmanned aerial vehicle |
| CN114426097A (en) * | 2022-02-23 | 2022-05-03 | 中煤航测遥感集团有限公司 | Unmanned aerial vehicle for surveying landform and landform |
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| CN113335496A (en) * | 2021-06-19 | 2021-09-03 | 国网浙江省电力有限公司浦江县供电公司 | Be applied to unmanned aerial vehicle horn subassembly that electric power cruises |
| CN114426097A (en) * | 2022-02-23 | 2022-05-03 | 中煤航测遥感集团有限公司 | Unmanned aerial vehicle for surveying landform and landform |
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| Publication number | Publication date |
|---|---|
| WO2019062140A1 (en) | 2019-04-04 |
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