CN204737022U - Unmanned vehicles - Google Patents

Unmanned vehicles Download PDF

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Publication number
CN204737022U
CN204737022U CN201520289259.2U CN201520289259U CN204737022U CN 204737022 U CN204737022 U CN 204737022U CN 201520289259 U CN201520289259 U CN 201520289259U CN 204737022 U CN204737022 U CN 204737022U
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CN
China
Prior art keywords
arm
gear
unmanned vehicle
rotary sleeve
aircraft
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.)
Expired - Fee Related
Application number
CN201520289259.2U
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Chinese (zh)
Inventor
杜树旺
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Zhijiang College of ZJUT
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Zhijiang College of ZJUT
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Filing date
Publication date
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Priority to CN201520289259.2U priority Critical patent/CN204737022U/en
Application granted granted Critical
Publication of CN204737022U publication Critical patent/CN204737022U/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Abstract

The utility model discloses an unmanned vehicles, including the aircraft body, and install camera on the aircraft body, unmanned vehicles still includes a plurality of folding arm components, every the arm component is including the first arm, the second arm and third arm that connect gradually, all install the wing on the first arm, second arm and the third arm, the first arm with the integrative manufacturing of aircraft body forms, the first arm with install a slewing mechanism between the second arm, the second arm with install the 2nd slewing mechanism between the third arm. The utility model discloses a last device of taking photo by plane of installing collapsible arm component structure of unmanned vehicles during the use, can change its external dimension so that should take photo by plane the device to can adapt to different flight spaces, and then make the device of taking photo by plane has the characteristics that convenient operation is swift, the application wide, adaptability is wide.

Description

Unmanned vehicle
Technical field
The utility model relates to a kind of unmanned vehicle.
Background technology
Unmanned vehicle has that volume is little, lightweight, expense is low, flexible operation and the high feature of safety, can be widely used in, monitor, search and rescue, the field such as resource exploration.
Multiaxis unmanned vehicle of the prior art generally includes aircraft body, the camera be arranged on aircraft body, and is arranged on multiple horns of aircraft body surrounding; Each horn is all provided with wing.But, the horn of existing multiaxis unmanned vehicle is generally relatively-stationary structure, when flight space or environment change (such as flight space diminishes) of multiaxis unmanned vehicle, because the oad of multiaxis unmanned vehicle can not change, and multiaxis unmanned vehicle is made to be difficult to use in the flight space diminished.
Utility model content
The purpose of this utility model there are provided a kind of unmanned vehicle, comprises aircraft body, and is arranged on the camera on described aircraft body, the equipment of taking photo by plane of common composition complete set.During use, this unmanned vehicle can be made to change its overall dimensions, thus different flight spaces can be adapted to, and then the equipment of taking photo by plane described in making has, and convenient to operation, application is wide, the feature of wide adaptability.
For achieving the above object, the technical solution of the utility model is:
A kind of unmanned vehicle, comprises aircraft body, and is arranged on the camera on described aircraft body; Described unmanned vehicle also comprises multiple folding arm component; Each described arm component comprises the first arm, the second arm and the 3rd arm that connect successively; Described first arm, the second arm and the 3rd arm are all provided with wing; Described first arm and described aircraft body is integrally manufactured forms; Between described first arm and described second arm, the first rotating mechanism is installed; Between described second arm and described 3rd arm, the second rotating mechanism is installed; Wherein,
Described first rotating mechanism comprises the first anchor shaft, and on the outer wall of the first described anchor shaft, rotary sleeve is equipped with the first rotary sleeve, and the outer wall of the first described rotary sleeve is coaxially installed with transmission gear; The first described rotating mechanism also comprises the motor be arranged on described first arm, is provided with gear cluster and the control device of wireless for controlling described electric machine rotation between described motor and described transmission gear;
Described second rotating mechanism comprises the second anchor shaft, and on the outer wall of the second described anchor shaft, rotary sleeve is equipped with the second rotary sleeve, and the second described rotary sleeve is positioned at described 3rd arm one end; Described second rotary sleeve and described second anchor shaft frictional fit.
Described gear cluster comprises the first gear, annular rack, the second gear and the 3rd gear; The rotating shaft of wherein said motor is set with the first gear; Described first arm is rotatablely equipped with annular rack, and described annular rack and the first gears meshing are installed; Described annular rack and the second gear are coaxially installed; Described second gear is provided with the 3rd gear with engaging between described transmission gear.
The number of teeth of described annular rack is greater than the number of teeth of described second gear.
Described transmission gear, the first gear, the second gear and the 3rd gear are spur wheel.
The surrounding of described aircraft body is evenly equipped with 4 arm components.
Described aircraft body is rotatablely equipped with camera.
The beneficial effects of the utility model are: unmanned vehicle of the present utility model adopts the structure of folding arm component, during use, this unmanned vehicle can be made to change its overall dimensions, thus different flight spaces can be adapted to, and then make the application of described unmanned vehicle wider; Moreover, the first rotating mechanism in employing arm component and the structure of the second rotating mechanism, when unmanned vehicle is in flight course, can control the first rotating mechanism action to change the overall dimensions of described unmanned vehicle by remote control equipment (RCE), it is convenient to operation, and comformability is wider; When unmanned vehicle is in stopped status, manually can rotate the second rotating mechanism to change the overall dimensions of described unmanned vehicle, its operation is convenient and swift equally.
Accompanying drawing explanation
Fig. 1 is the perspective view of the unmanned vehicle that the utility model preferred embodiment provides;
Fig. 2 is the inside amplification assumption diagram of the arm component in the unmanned vehicle shown in Fig. 1;
Fig. 3 is the inside amplification assumption diagram of the first rotating mechanism in the unmanned vehicle shown in Fig. 1;
Fig. 4 is the partial enlargement constructional drawing of the first rotating mechanism in the unmanned vehicle shown in Fig. 1;
Fig. 5 is the inside amplification assumption diagram of the second rotating mechanism in the unmanned vehicle shown in Fig. 1.
Detailed description of the invention
As shown in Figure 1 and Figure 2, a kind of unmanned vehicle of the present embodiment, it comprises aircraft body 1, camera 2, arm component 3 and wing 4.
Particularly, as shown in Figure 1, this aircraft body 1 is the main element of unmanned vehicle, and it is structure common in prior art, does not repeat them here.This camera 2 is arranged on the below of aircraft body 1, and preferably, camera 2 is installed in rotation on aircraft body 1, and the coverage of camera 2 can be made wider.
As shown in Figure 1 and Figure 2, arm component 3 is provided with multiple, and it is arranged on the surrounding of aircraft body 1.In the present embodiment, preferably, arm component 3 is 4, and 4 arm components 3 are evenly distributed in the surrounding of aircraft body 1.Arm component 3 comprises the first arm 31, second arm 32, the 3rd arm 33, first rotating mechanism 34 and the second rotating mechanism 35.
Wherein, first arm 31, second arm 32, the 3rd arm 33 are roughly the structure of vertical bar shaped, first arm 31 forms with aircraft body 1 is integrally manufactured, each first arm 31, each second arm 32 and each 3rd arm 33 are all provided with wing 4, first arm 31, second arm 32 and the rotational plane of the 3rd arm 33 and the rotating shaft of wing 4 mutually vertical, this wing 4 is structure common in prior art, does not repeat them here.
Consult shown in Fig. 2 as Fig. 3, Fig. 4, described first arm 31 is connected by the first rotating mechanism 34 with between the second arm 32, to realize both being rotationally connected.In the present embodiment, the first rotating mechanism 34 comprises the first anchor shaft 341, first rotary sleeve 342, transmission gear 343, motor 344 and gear cluster 345.
The first anchor shaft 341 in the present embodiment is roughly cylindrical-shaped structure, is provided with the first anchor shaft 341 on described first arm 31 and away from one end of aircraft body 1, in the present embodiment, and the first anchor shaft 341 and the first arm 31 is integrally manufactured forms.First rotary sleeve 342 is roughly the circular ring structure of hollow, and on the outer wall being provided with the first rotary sleeve 342, first anchor shaft 341 on described second arm 32 and away from one end of the 3rd arm 33, rotary sleeve is equipped with the first rotary sleeve 342.In the present embodiment, the first rotary sleeve 342 and the second arm 32 is integrally manufactured forms.Described first rotary sleeve 342 outer wall is coaxially installed with transmission gear 343 with the first rotary sleeve 342, the outer circumference of also i.e. the first rotary sleeve 342 offers and the coaxial gear structure arranged of the first rotary sleeve 342.In the present embodiment, transmission gear 343 is spur wheel, and the rotating shaft of itself and wing 4 is coaxially arranged.Described first arm 31 is also provided with motor 344, and it rotates for being with nutating gear 343.
Be connected with gear cluster 345 between described motor 344 and transmission gear 343, particularly, gear cluster 345 comprises the first gear 3451, annular rack 3452, second gear 3453 and the 3rd gear 3454.Wherein, the rotating shaft of motor 344 is set with the first gear 3451, first arm 31 is rotatablely equipped with annular rack 3452, and described annular rack 3452 engages with the first gear 3451 and installs, described annular rack 3452 and the second gear 3453 are coaxially installed, and the 3rd gear 3454 is provided with the second gear 3453 with engaging between transmission gear 343.In the present embodiment, the number of teeth of annular rack 3452 is greater than the number of teeth of the second gear 3453, and also namely annular rack 3452 and the second gear 3453 form train of reduction gears, to play the effect of deceleration.Preferably, the first gear 3451, second gear 3453 and the 3rd gear 3454 are spur wheel, and its structure is simple, and cost is lower.
In the present embodiment, first rotating mechanism 34 also comprises the control device of wireless (not shown) rotated for controlling motor 344, the remote controller (not shown) of described unmanned vehicle can this control device of wireless of wireless operated, to make user can the rotation of Control arm assembly 3 in described unmanned vehicle flight course, to change the oad of described unmanned vehicle, its operation is comparatively easy.This control device of wireless is structure common in prior art, does not repeat them here.
Consult shown in Fig. 2 as Fig. 5, the second rotating mechanism 35 comprises the second anchor shaft 351 and the second rotary sleeve 352.Second anchor shaft 351 is roughly cylindrical-shaped structure, and the second rotary sleeve 352 is roughly the circular ring structure of hollow, and on the outer wall of the second anchor shaft 351, rotary sleeve is equipped with the second rotary sleeve 352.The second described arm 32 is provided with the second anchor shaft 351, and the second described arm 32 and the second anchor shaft 351 is integrally manufactured forms; The 3rd described arm 33 is provided with the second rotary sleeve 352, and the 3rd described arm 33 and the second rotary sleeve 352 is integrally manufactured forms.In the present embodiment, the second rotary sleeve 352 and the second anchor shaft 351 frictional fit.When rotation the 3rd arm 33 and the second arm 32 form certain angle, by the friction force between the second rotary sleeve 352 and the second anchor shaft 351, the 3rd arm 33 and the second arm 32 also can be made to keep relatively-stationary state, and then change the oad of arm component 3.In the present embodiment, when described unmanned vehicle is in stopped status, manually can rotate the second rotating mechanism 35 to change the overall dimensions of described unmanned vehicle, its operation is comparatively convenient and swift.
Use the unmanned vehicle that as above embodiment provides, because described unmanned vehicle adopts collapsible arm assembly 3 structure, during use, this unmanned vehicle can be made to change its overall dimensions, thus different flight spaces can be adapted to, and then make the application of described unmanned vehicle wider; Moreover, the first rotating mechanism 34 in employing arm component 3 and the structure of the second rotating mechanism 35, when unmanned vehicle is in flight course, the first rotating mechanism 34 action can be controlled to change the overall dimensions of described unmanned vehicle by remote control equipment (RCE), it is convenient to operation, and comformability is wider; When unmanned vehicle is in stopped status, manually can rotate the second rotating mechanism 35 to change the overall dimensions of described unmanned vehicle, its operation is convenient and swift equally.In the present embodiment, arm component 3 can manually or electronic mode to change its oad, when user is used operation easier.

Claims (7)

1. a unmanned vehicle, comprises aircraft body (1), and is arranged on the camera (2) on described aircraft body (1); It is characterized in that: described unmanned vehicle also comprises folding arm component (3); Described arm component (3) comprises the first arm (31), the second arm (32) and the 3rd arm (33) that connect successively; Described first arm (31), the second arm (32) and the 3rd arm (33) are all provided with wing (4); Described first arm (31) forms with described aircraft body (1) is integrally manufactured; Between described first arm (31) and described second arm (32), the first rotating mechanism (34) is installed; Between described second arm (32) and described 3rd arm (33), the second rotating mechanism (35) is installed; Wherein,
Described first rotating mechanism (34) comprises the first anchor shaft (341), on the outer wall of described the first anchor shaft (341), rotary sleeve is equipped with the first rotary sleeve (342), and the outer wall of described the first rotary sleeve (342) is coaxially installed with transmission gear (343); Described the first rotating mechanism (34) also comprises the motor (344) be arranged on described first arm (31), is provided with gear cluster (345) and for controlling the control device of wireless that described motor (344) rotates between described motor (344) and described transmission gear (343);
Described second rotating mechanism (35) comprises the second anchor shaft (351), and on the outer wall of described the second anchor shaft (351), rotary sleeve is equipped with the second rotary sleeve (352), and described the second rotary sleeve (352) is positioned at described 3rd arm (33) one end; Described second rotary sleeve (352) and described second anchor shaft (351) frictional fit.
2. unmanned vehicle according to claim 1, is characterized in that: described transmission gear (343) is coaxially installed with the rotating shaft of the wing (4) on the first arm (31); Described the first arm (31) is provided with the first anchor shaft (341), and described the first arm (31) forms with the first anchor shaft (341) is integrally manufactured; Described the second arm (32) is provided with the first rotary sleeve (342), and described the second arm (32) forms with the first rotary sleeve (342) is integrally manufactured; Described the second arm (32) is provided with the second anchor shaft (351), and described the second arm (32) forms with the second anchor shaft (351) is integrally manufactured; The 3rd described arm (33) is provided with the second rotary sleeve (352), and the 3rd described arm (33) forms with the second rotary sleeve (352) is integrally manufactured.
3. unmanned vehicle according to claim 1, is characterized in that: described gear cluster (345) comprises the first gear (3451), annular rack (3452), the second gear (3453) and the 3rd gear (3454); The rotating shaft of wherein said motor (344) is set with the first gear (3451); Described first arm (31) is rotatablely equipped with annular rack (3452), and described annular rack (3452) engages with the first gear (3451) and installs; Described annular rack (3452) and the second gear (3453) are coaxially installed; Described second gear (3453) is provided with the 3rd gear (3454) with engaging between described transmission gear (343).
4. unmanned vehicle according to claim 3, is characterized in that: the number of teeth of described annular rack (3452) is greater than the number of teeth of described second gear (3453).
5. unmanned vehicle according to claim 3, is characterized in that: described transmission gear (343), the first gear (3451), the second gear (3453) and the 3rd gear (3454) are spur wheel.
6. unmanned vehicle according to claim 1, is characterized in that: the surrounding of described aircraft body (1) is evenly equipped with 4 arm components (3).
7. unmanned vehicle according to claim 1, is characterized in that: described aircraft body (1) is rotatablely equipped with camera (2).
CN201520289259.2U 2015-05-06 2015-05-06 Unmanned vehicles Expired - Fee Related CN204737022U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201520289259.2U CN204737022U (en) 2015-05-06 2015-05-06 Unmanned vehicles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201520289259.2U CN204737022U (en) 2015-05-06 2015-05-06 Unmanned vehicles

Publications (1)

Publication Number Publication Date
CN204737022U true CN204737022U (en) 2015-11-04

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201520289259.2U Expired - Fee Related CN204737022U (en) 2015-05-06 2015-05-06 Unmanned vehicles

Country Status (1)

Country Link
CN (1) CN204737022U (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104859836A (en) * 2015-05-06 2015-08-26 浙江工业大学之江学院 Unmanned aerial vehicle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104859836A (en) * 2015-05-06 2015-08-26 浙江工业大学之江学院 Unmanned aerial vehicle

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C14 Grant of patent or utility model
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20151104

Termination date: 20180506

CF01 Termination of patent right due to non-payment of annual fee