CN204822066U - Aircraft - Google Patents

Aircraft Download PDF

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Publication number
CN204822066U
CN204822066U CN201520516332.5U CN201520516332U CN204822066U CN 204822066 U CN204822066 U CN 204822066U CN 201520516332 U CN201520516332 U CN 201520516332U CN 204822066 U CN204822066 U CN 204822066U
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CN
China
Prior art keywords
aircraft
pivoted arm
locating dowel
dowel pin
cover
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
Application number
CN201520516332.5U
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Chinese (zh)
Inventor
陈思达
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.)
Guangdong brightness fine horse science and technology Group Co., Ltd
Original Assignee
Shenzhen Qianhai Territory Intelligent Technology Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Shenzhen Qianhai Territory Intelligent Technology Co Ltd filed Critical Shenzhen Qianhai Territory Intelligent Technology Co Ltd
Priority to CN201520516332.5U priority Critical patent/CN204822066U/en
Application granted granted Critical
Publication of CN204822066U publication Critical patent/CN204822066U/en
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Abstract

The utility model is suitable for an aircraft technical field provides an aircraft, including aircraft body and rocking arm, the one end of rocking arm connect in the aircraft body, the other end of rocking arm is connected with the screw subassembly, the rocking arm with rotate between the aircraft body and connect, the rocking arm with be provided with between the aircraft body be used for with the rocking arm lock in the angle stop device of aircraft body, angle stop device including connect in rocking arm or aircraft body with carry on the spacing locating pin of angle with connect in rocking arm or aircraft body just are used for the drive the locating pin makes spacing unblock button is relieved to the locating pin. The utility model provides an aircraft, its rocking arm can launch and draw in between switch over, operate ten fens reliable and simple, need not appurtenance, the user's of being convenient for use.

Description

Aircraft
Technical field
The utility model belongs to vehicle technology field, particularly relates to a kind of aircraft.
Background technology
Aircraft of the prior art, such as the unmanned plane in fields such as taking photo by plane, its screw propeller assembly is connected to pivoted arm, pivoted arm is connected to aircraft body, aircraft of the prior art, its pivoted arm launches, draw inconvenient operation in, generally needs to adopt the accessory appliancess such as screwdriver to carry out, and is not easy to the use of user.
Utility model content
The purpose of this utility model is to overcome above-mentioned the deficiencies in the prior art, provides a kind of aircraft, and its pivoted arm launches, it is easy to operate to draw in, is convenient to the use of user.
The utility model is achieved in that a kind of aircraft, comprise aircraft body and pivoted arm, one end of described pivoted arm is connected to described aircraft body, the other end of described pivoted arm is connected with screw propeller assembly, being rotationally connected between described pivoted arm and described aircraft body, between described pivoted arm and described aircraft body, being provided with the angular stop means for pivoted arm being locked in described aircraft body; Described angular stop means comprises and is connected to described pivoted arm or/and aircraft body is to carry out the locating dowel pin of angle limit and to be connected to described pivoted arm or/and aircraft body and for driving described locating dowel pin and making described locating dowel pin remove spacing release tab.
Alternatively, described locating dowel pin is slidably connected to described aircraft body, and described pivoted arm is provided with has two spacing holes that can insert for described locating dowel pin in rotation direction at least.
Alternatively, described release tab is slidably connected to described pivoted arm, and described release tab is connected with at least two button posts inserted respectively in described spacing hole.
Alternatively, described pin bush is provided with elastic component, and described aircraft body is connected with the compressing tablet for compressing described elastic component, and one end of described elastic component is placed on described locating dowel pin, and the other end of described elastic component is resisted against described compressing tablet.
Alternatively, axle sleeve is provided with between described pivoted arm and described aircraft body; The upper end of described axle sleeve is or/and lower end is provided with wear plate.
Alternatively, described pivoted arm has shaft, described aircraft body has the connecting bore for wearing for described shaft, described aircraft body is connected with fixed block, fixed piece is connected with lower fixed block, fixed piece is provided with spacing deep-slotted chip breaker, and described shaft is one-body molded, and have can along the projection of described spacing arc sliding.
Alternatively, the below of described release tab is provided with the return unit for making described release tab reset.
Alternatively, described pivoted arm comprises upper cover and lower cover, and described upper cover and the involutory setting of described lower cover are also formed with container cavity, are provided with circuit card and illuminating part in described container cavity, and described upper cover is or/and the corresponding described illuminating part place of lower cover is connected with lampshade.
Alternatively, described screw propeller assembly comprises motor, and described motor is fixedly connected on described pivoted arm, and described motor is fixedly connected with briquetting parts, and described briquetting parts are rotatably connected at least two and can turn to screw propeller that is overlapping up and down with pivoted arm and that rotatably launch.
Alternatively, the angle of two corresponding described pivoted arm center of turns of described spacing hole is 90 to 135 degree.
Aircraft provided by the utility model, the angular stop means for pivoted arm being locked in described aircraft body is provided with between its pivoted arm and described aircraft body, with by the angular definitions of pivoted arm launch and draw in state, prevent aircraft in use procedure or deposit pivoted arm in process and arbitrarily rotate voluntarily, of good reliability, by being unlocked by pressing button, the locking of locating dowel pin releasing to pivoted arm can be made, pivoted arm relative flight device body can be made to rotate, until pivoted arm locks by locating dowel pin again, pivoted arm can switch between expansion and gathering, operate very simple, without the need to accessory appliances, be convenient to the use of user.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the embodiment of the present invention, be briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the perspective exploded view of the aircraft that the utility model embodiment provides;
Fig. 2 is perspective exploded view when pivoted arm draws in the aircraft that provides of the utility model embodiment;
Fig. 3 is the perspective exploded view in the aircraft that provides of the utility model embodiment in pivoted arm expansion process;
Perspective exploded view when Fig. 4 is pivoted arm expansion process in the aircraft that provides of the utility model embodiment;
Perspective exploded view when Fig. 5 is pivoted arm expansion process in the aircraft that provides of the utility model embodiment;
Fig. 6 is the perspective exploded view in the aircraft that provides of the utility model embodiment in pivoted arm gathering process;
Fig. 7 is the perspective exploded view in the aircraft that provides of the utility model embodiment in pivoted arm gathering process.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
It should be noted that, when element is called as " being fixed on " or " being arranged at " another element, it can directly on another element or may there is centering elements simultaneously.When an element is known as " being connected to " another element, it can be directly connected to another element or may there is centering elements simultaneously.
Also it should be noted that, the orientation term such as left and right, upper and lower in the utility model embodiment, is only relative concept or be reference with the normal operating condition of product each other, and should not be regarded as have restrictive.
As shown in Fig. 1 ~ Fig. 7, a kind of aircraft that the utility model embodiment provides, aircraft can be unmanned plane, comprise aircraft body 1(aircraft drain pan, local is only shown in figure) and pivoted arm 2, one end of described pivoted arm 2 is connected to described aircraft body 1, and the other end of described pivoted arm 2 is connected with screw propeller assembly 3.Be rotationally connected between described pivoted arm 2 and described aircraft body 1, pivoted arm 2 can launch and draw in by relative flight device body 1.The angular stop means for pivoted arm 2 being locked in described aircraft body 1 is provided with between described pivoted arm 2 and described aircraft body 1, with by the angular definitions of pivoted arm 2 launch and draw in state, prevent aircraft in use procedure or deposit pivoted arm 2 in process and arbitrarily rotate voluntarily, of good reliability; Described angular stop means comprises and is connected to described pivoted arm 2 or/and aircraft body 1 is to carry out the locating dowel pin 41 of angle limit and to be connected to described pivoted arm 2 or/and aircraft body 1 and for driving described locating dowel pin 41 and making described locating dowel pin 41 remove spacing release tab 42, by being unlocked by pressing button 42, locating dowel pin 41 can be made to remove locking to pivoted arm 2, pivoted arm 2 relative flight device body 1 can be made to rotate, until pivoted arm 2 locks by locating dowel pin 41 again, operate very simple, without the need to accessory appliances, be convenient to the use of user.
In the present embodiment, described locating dowel pin 41 is slidably connected to described aircraft body 1, described pivoted arm 2 is provided with has two spacing holes that can insert for described locating dowel pin 41 in rotation direction at least, and locating dowel pin 41 inserts different knock holees, and pivoted arm 2 can in the state launched or draw in.
Particularly, described release tab 42 is slidably connected to described pivoted arm 2, and described release tab 42 is connected with at least two button posts 43 inserted respectively in described spacing hole.By being unlocked by pressing button 42, thus button post 43 can be made synchronous with release tab 42 synchronous slide, and then make locating dowel pin 41 exit spacing hole, structure is ingenious, reliable.Button post 43 can be threadedly connected to release tab 42.
Particularly, described locating dowel pin 41 is arranged with elastic component 44, and described aircraft body 1 is connected with the compressing tablet 45 for compressing described elastic component 44, and one end of described elastic component 44 is placed on described locating dowel pin 41, and the other end of described elastic component 44 is resisted against described compressing tablet 45.Elastic component 44 can be spring.Compressing tablet 45 can be connected to aircraft body 1(by screw 451 and specifically can be the suitable places such as aircraft drain pan)
Particularly, between described pivoted arm 2 and described aircraft body 1, be provided with axle sleeve 46, to make the rotation of pivoted arm 2 more smooth and easy.
Particularly, the upper end of described axle sleeve 46 is or/and lower end is provided with wear plate 47, and structural reliability is high, and is beneficial to the service life extending product.
Particularly, described pivoted arm 2 has shaft 211, described aircraft body 1 has the connecting bore for wearing for described shaft 211, described aircraft body 1 is connected with fixed block 481, be connected with lower fixed block 481 for fixed piece 481, be provided with spacing deep-slotted chip breaker 480 for fixed piece 481, described shaft 211 is one-body molded, and have can along the projection 201 of described spacing arc sliding, projection 201 stretches in spacing deep-slotted chip breaker 480, to make to slide in the angular interval of the right restriction of pivoted arm 2, product reliability is good.
Specific requirement ground, the below of described release tab 42 is provided with the return unit 49 for making described release tab 42 reset.Return unit 49 can be spring etc., and when unclamping release tab 42, release tab 42 can automatically reset in time under the elastic reaction of return unit 49.
Particularly, described screw propeller assembly 3 comprises motor 31, described motor 31 is fixedly connected on described pivoted arm 2, and described motor 31 is fixedly connected with briquetting parts 32, and described briquetting parts 32 are rotatably connected at least two and can turn to screw propeller 33 that is overlapping with pivoted arm about 2 and that rotatably launch.Screw propeller 33 can turn to overlapping with pivoted arm 2, also can launch to use, and user can when using aircraft, and launched by screw propeller 33, product can normally use.Carrying, store, transporter aircraft time, each screw propeller 33 can be turned to receipts overlapping state overlapping up and down, the tailored appearance of screw propeller assembly 3 is light and handy, by adopting swiveling design, easily realize the expansion in screw propeller 33 flight course and the gathering in carrying process, it is little that product takies volume, thus make to carry, store more convenient.
Particularly, described pivoted arm 2 comprises upper cover 21 and lower cover 22, described upper cover 21 is with the involutory setting of described lower cover 22 and be formed with container cavity, circuit card 23 and illuminating part is provided with in described container cavity, illuminating part can be LED, described upper cover 21 is or/and the corresponding described illuminating part place of lower cover 22 is connected with lampshade 24, and to ensure lighting effects, circuit card 23 can be used for controlling motor 31, illuminating part etc.
Particularly, the angle of two corresponding described pivoted arm 2 center of turns of described spacing hole is 90 to 135 degree, in the present embodiment, the angle of two corresponding described pivoted arm 2 center of turns of described spacing hole is 128.5 degree, and namely pivoted arm 2 launches, angle between rounding state is 128.5 degree.In embody rule, pivoted arm 2 launches, angle between rounding state also can be set as other suitable angle, all belongs to protection domain of the present utility model.
The process launching pivoted arm 2 can with reference to as follows, being unlocked by pressing button 42, then rotate pivoted arm 2, launches completion status as shown in Figure 4,5, and the process of drawing pivoted arm 2 in can with reference to as follows, being unlocked by pressing button 42, then reflection rotates pivoted arm 2, draws completion status in as shown in Figure 2.
The aircraft that the utility model embodiment provides, the angular stop means for pivoted arm 2 being locked in described aircraft body 1 is provided with between its pivoted arm 2 and described aircraft body 1, with by the angular definitions of pivoted arm 2 launch and draw in state, prevent aircraft in use procedure or deposit pivoted arm 2 in process and arbitrarily rotate voluntarily, of good reliability; Described angular stop means comprises and is connected to described pivoted arm 2 or/and aircraft body 1 is to carry out the locating dowel pin 41 of angle limit and to be connected to described pivoted arm 2 or/and aircraft body 1 and for driving described locating dowel pin 41 and making described locating dowel pin 41 remove spacing release tab 42, by being unlocked by pressing button 42, locating dowel pin 41 can be made to remove locking to pivoted arm 2, pivoted arm 2 relative flight device body 1 can be made to rotate, until pivoted arm 2 locks by locating dowel pin 41 again, operate very simple, without the need to accessory appliances, be convenient to the use of user.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all do within spirit of the present utility model and principle any amendment, equivalent to replace or improvement etc., all should be included within protection domain of the present utility model.

Claims (10)

1. an aircraft, comprise aircraft body and pivoted arm, one end of described pivoted arm is connected to described aircraft body, the other end of described pivoted arm is connected with screw propeller assembly, it is characterized in that, being rotationally connected between described pivoted arm and described aircraft body, between described pivoted arm and described aircraft body, being provided with the angular stop means for pivoted arm being locked in described aircraft body; Described angular stop means comprises and is connected to described pivoted arm or/and aircraft body is to carry out the locating dowel pin of angle limit and to be connected to described pivoted arm or/and aircraft body and for driving described locating dowel pin and making described locating dowel pin remove spacing release tab.
2. aircraft as claimed in claim 1, it is characterized in that, described locating dowel pin is slidably connected to described aircraft body, and described pivoted arm is provided with has two spacing holes that can insert for described locating dowel pin in rotation direction at least.
3. aircraft as claimed in claim 1, it is characterized in that, described release tab is slidably connected to described pivoted arm, and described release tab is connected with at least two button posts inserted respectively in described spacing hole.
4. aircraft as claimed in claim 1, it is characterized in that, described pin bush is provided with elastic component, and described aircraft body is connected with the compressing tablet for compressing described elastic component, one end of described elastic component is placed on described locating dowel pin, and the other end of described elastic component is resisted against described compressing tablet.
5. aircraft as claimed in claim 1, is characterized in that, be provided with axle sleeve between described pivoted arm and described aircraft body; The upper end of described axle sleeve is or/and lower end is provided with wear plate.
6. aircraft as claimed in claim 1, it is characterized in that, described pivoted arm has shaft, described aircraft body has the connecting bore for wearing for described shaft, described aircraft body is connected with fixed block, fixed piece is connected with lower fixed block, and fixed piece is provided with spacing deep-slotted chip breaker, and described shaft is one-body molded, and have can along the projection of described spacing arc sliding.
7. the aircraft according to any one of claim 1 to 6, is characterized in that, the below of described release tab is provided with the return unit for making described release tab reset.
8. the aircraft according to any one of claim 1 to 6, it is characterized in that, described pivoted arm comprises upper cover and lower cover, described upper cover and the involutory setting of described lower cover are also formed with container cavity, be provided with circuit card and illuminating part in described container cavity, described upper cover is or/and the corresponding described illuminating part place of lower cover is connected with lampshade.
9. the aircraft according to any one of claim 1 to 6, it is characterized in that, described screw propeller assembly comprises motor, described motor is fixedly connected on described pivoted arm, described motor is fixedly connected with briquetting parts, and described briquetting parts are rotatably connected at least two and can turn to screw propeller that is overlapping up and down with pivoted arm and that rotatably launch.
10. aircraft as claimed in claim 2, is characterized in that, the angle of two corresponding described pivoted arm center of turns of described spacing hole is 90 to 135 degree.
CN201520516332.5U 2015-07-16 2015-07-16 Aircraft Active CN204822066U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201520516332.5U CN204822066U (en) 2015-07-16 2015-07-16 Aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201520516332.5U CN204822066U (en) 2015-07-16 2015-07-16 Aircraft

Publications (1)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107521656A (en) * 2016-06-22 2017-12-29 北京臻迪机器人有限公司 A kind of retaining mechanism of aircraft horn
WO2020000677A1 (en) * 2018-06-28 2020-01-02 深圳市大疆创新科技有限公司 Unmanned aerial vehicle and machine frame thereof

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107521656A (en) * 2016-06-22 2017-12-29 北京臻迪机器人有限公司 A kind of retaining mechanism of aircraft horn
WO2020000677A1 (en) * 2018-06-28 2020-01-02 深圳市大疆创新科技有限公司 Unmanned aerial vehicle and machine frame thereof

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Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
CP03 Change of name, title or address
CP03 Change of name, title or address

Address after: 518101, F7 building 1065, F518 creative garden, No. 201, Po Yuen Road, Xixiang street, Shenzhen, Guangdong, Baoan District

Patentee after: Shenzhen territory intelligent Polytron Technologies Inc

Address before: 518100 Guangdong city of Shenzhen province Qianhai cooperation zone before the Deep Bay Road No. 1 building 201 room A

Patentee before: SHENZHEN QIANHAI TERRITORY INTELLIGENT TECHNOLOGY CO., LTD.

TR01 Transfer of patent right
TR01 Transfer of patent right

Effective date of registration: 20190419

Address after: 514400 Industrial Park of Shuizhai Town, Wuhua County, Meizhou City, Guangdong Province

Patentee after: Guangdong brightness fine horse science and technology Group Co., Ltd

Address before: 518101 F7 Building 201, F518 Creative Park, 1065 Baoyuan Road, Xixiang Street, Baoan District, Shenzhen City, Guangdong Province

Patentee before: Shenzhen territory intelligent Polytron Technologies Inc