CN220884821U

CN220884821U - Modularized miniature unmanned aerial vehicle stable in hovering

Info

Publication number: CN220884821U
Application number: CN202322537799.5U
Authority: CN
Inventors: 聂勇; 陈联
Original assignee: Shenzhen Haming Technology Co ltd
Current assignee: Shenzhen Haming Technology Co ltd
Priority date: 2023-09-18
Filing date: 2023-09-18
Publication date: 2024-05-03
Anticipated expiration: 2033-09-18

Abstract

The utility model discloses a modularized micro unmanned aerial vehicle with hover stability, which comprises a frame, four rotating mechanisms, a picture transmission camera module, a flight control main board, a division board, a battery assembly, an optical flow sensor and a laser sensor, wherein the frame is provided with a plurality of rotary units; the optical flow sensor and the laser sensor are arranged on the split plate and are electrically connected to the flight control main board through a pin header; the whole machine flip-chip is realized to the frame main part of moulding plastics that adopts an organic whole, and each part of easy to assemble lightens whole weight, make full use of limited space, wherein, optical flow sensor and laser sensor install on the minute board and are connected in flying accuse mainboard through the row's of needle electricity, have effectively avoided the sensor to receive the influence of flying accuse mainboard temperature rise, electromagnetic etc. interference, simultaneously, place this image sensor module at the front end of frame main part and fly accuse mainboard and separate, avoided the problem that the temperature rise is concentrated effectively to make installation and dismantlement become more convenient.

Description

Modularized miniature unmanned aerial vehicle stable in hovering

Technical Field

The utility model relates to the unmanned aerial vehicle field technology, in particular to a modularized miniature unmanned aerial vehicle with hover stability.

Background

With the technical development of unmanned aerial vehicles, unmanned aerial vehicles can help people in certain fields, and various unmanned aerial vehicle and application functions are realized; at present, unmanned aerial vehicles have realized wide application in fields such as aerial photography, agriculture, plant protection, miniature self-timer, express delivery transportation, disaster rescue, wild animal observation and the like.

The unmanned aerial vehicle in the traditional technology has a plurality of defects on its own structure, for example:

1. The existing micro unmanned plane is limited by small volume, the integration level is not high enough, and in order to integrate more modules, more wires are needed to be connected, but the connection is easy to be unstable or broken, and the flight stability and data transmission are affected;

2. the sensing recognition performance of the existing micro unmanned aerial vehicle is not stable enough, because the sensor is directly fixed on the flight control main board, the sensor is easily affected by temperature rise and electromagnetic interference;

3. The existing forward-mounted micro unmanned aerial vehicle mainly concentrates modules such as a flight control board, a picture transmission board, a camera and the like at the top cover position, and the problems of insufficient heat dissipation, electromagnetic interference and the like can occur;

4. Under the structure of the fixed motor of the carbon fiber plate, the horizontal plane of the plastic structural part for installing 4 motors is affected by insufficient structural form and strength, and the motor is easy to be uneven in height.

Therefore, a new technical solution is needed to solve the above problems.

Disclosure of utility model

In view of the above, the main object of the present utility model is to provide a modularized micro unmanned aerial vehicle with stable hovering, which adopts an integral injection molding frame main body to realize complete machine inversion, so as to facilitate installation of each component, reduce overall weight, and fully utilize limited space, wherein an optical flow sensor and a laser sensor are installed on a split board and electrically connected to a flight control main board through a pin header, thereby effectively avoiding the influence of the sensor caused by the temperature rise of the flight control main board, electromagnetic interference and the like, and simultaneously, the image pickup module is placed at the front end of the frame main body to be separated from the flight control main board, thereby effectively avoiding the problem of concentrated temperature rise, and facilitating installation and disassembly.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

A modularized miniature unmanned aerial vehicle with stable hovering comprises a frame, four rotating mechanisms, a picture transmission camera module, a flight control main board, a division board, a battery assembly, an optical flow sensor and a laser sensor, wherein the optical flow sensor and the laser sensor are used for increasing the stability and safety of the unmanned aerial vehicle hovering and flying; the four rotating mechanisms, the battery assembly, the image transmission and shooting module, the sub-board, the optical flow sensor and the laser sensor are all electrically connected to the flight control main board, wherein the optical flow sensor and the laser sensor are arranged on the sub-board and are electrically connected to the flight control main board through a pin header;

The frame comprises a frame main body and a fixed plate, wherein the frame main body is of an integral injection molding structure, and a first setting position for installing a picture-transmission camera module, a second setting position for installing and positioning a battery component, a third setting position for installing four rotating mechanisms and a fourth setting position for installing and positioning a flight control main board are respectively arranged on the frame main body; the first setting position, the second setting position, the third setting position and the fourth setting position are mutually connected; the first positioning position and the second positioning position are positioned on the upper end face of the frame main body, and the first positioning position is concavely arranged from the upper end of the frame main body; the fourth setting position is concavely arranged inwards from the lower end face of the frame main body and is arranged back to the second setting position;

The image transmission camera module is arranged in the first setting position; the battery assembly is arranged in the second setting position; the four rotating mechanisms are inversely arranged in a third setting position; the flight control main board is locked in the fourth setting position through the fixing board.

As a preferred scheme, the image transmission camera module comprises a camera, an image transmission plate and a support, wherein the camera is arranged on the support, one end of the camera is electrically connected with the image transmission plate through a 3PIN row PIN, and the image transmission plate is electrically connected with the flight control main plate.

As a preferable scheme, a first butt joint part is arranged in the first positioning position, correspondingly, a second butt joint part is arranged on the support corresponding to the first butt joint part, and the support respectively penetrates through the first butt joint part and the second butt joint part through a first screw to be fixedly arranged in the first positioning position.

As a preferred scheme, be provided with two joint grooves on the second location, correspondingly, battery pack is including battery and mounting bracket, the battery is installed in the mounting bracket, the periphery side of mounting bracket is provided with two joint portions that are used for with two joint groove looks adaptations, battery pack installs in the second location, two joint portions detain and locate in two joint grooves.

As a preferred scheme, be provided with a plurality of first spliced poles and a plurality of second spliced pole in the fourth arrangement position respectively, correspondingly, the department that corresponds first spliced pole on the accuse mainboard that flies is provided with first connecting hole, the department that corresponds the second spliced pole on the fixed plate is provided with the second connecting hole, the accuse mainboard that flies is installed in the fourth arrangement position, first connecting hole adaptation is in first spliced pole, the fixed plate passes second connecting hole and second spliced pole lock solid frame main part's bottom terminal surface respectively through the second screw.

As a preferred scheme, still be provided with a plurality of extension arms on the frame main part, the one end of a plurality of extension arms is connected in the one end of first position, second position and third position respectively, a plurality of extension arms are hollow triangle-shaped.

As a preferable scheme, the plurality of extension arms are provided with wire passing grooves for wiring, and wire passing holes are formed in the side walls of the wire passing grooves.

As a preferred scheme, the rotating mechanism comprises a motor and a blade connected to the bottom of the motor, and the blade is inversely arranged in the third setting position.

Compared with the prior art, the utility model has obvious advantages and beneficial effects, in particular, the technical proposal can realize the whole machine inversion by adopting an integral injection molding frame main body through the structural design among the frame, four rotating mechanisms, the image transmission and shooting module, the flight control main board, the division board, the battery component, the optical flow sensor and the laser sensor, thereby facilitating the installation of all components, reducing the overall weight and fully utilizing the limited space;

The optical flow sensor and the laser sensor are arranged on the split plate and are electrically connected to the flight control main plate through the pin header, so that the influence of temperature rise, electromagnetic interference and the like of the flight control main plate on the sensor is effectively avoided, the risks of blocked and abnormal operation of the sensor are reduced, the optical flow sensor is utilized for carrying out image processing by utilizing the change of images and detecting the state of the ground, the speed and the position change of the unmanned aerial vehicle are monitored, the laser sensor is utilized for calculating the relative position between the unmanned aerial vehicle and the ground, the stability and the safety of hovering flight are obviously enhanced, and more accurate hovering and control capability is provided;

The design of the image transmission and shooting module reduces the volume of the image transmission and shooting module and the number of connecting wires, and meanwhile, the image transmission and shooting module is placed at the front end of the frame main body and separated from the flight control main board, so that the problem of concentrated temperature rise is effectively avoided, and the installation and the disassembly become more convenient.

In order to more clearly illustrate the structural features and efficacy of the present utility model, the present utility model will be described in detail below with reference to the accompanying drawings and examples.

Drawings

FIG. 1 is a perspective view of an embodiment of the present utility model;

FIG. 2 is an exploded view of an embodiment of the present utility model

FIG. 3 is another exploded view of an embodiment of the present utility model;

fig. 4 is yet another exploded view of an embodiment of the present utility model.

The attached drawings are used for identifying and describing:

10. Frame 11, frame body

12. The fixed plate 13, the first setting position

121. Second connecting hole

14. Second setting bit 15, third setting bit

16. Fourth setting bit 131, first butt joint

141. Clamping groove 161 and first connecting column

162. Second connecting column 17, extension arm

171. Wire passing groove 172 and wire passing hole

20. Rotation mechanism 21 and motor

22. Blade 30 and image transmission camera module

31. Camera 32, image transmission plate

33. Bracket 34, 3PIN row needle

331. Second butt joint part 40 and flight control main board

41. First connecting hole 50, split plate

60. Battery pack 61, battery

62. Mounting bracket 621, joint portion

70. Optical flow sensor 80, laser sensor.

Detailed Description

Referring to fig. 1 to 4, specific structures of embodiments of the present utility model are shown.

In the description of the present utility model, it should be noted that, for the azimuth words, terms such as "upper", "lower", "front", "rear", "left", "right", etc., indicate azimuth and positional relationships as shown based on the drawings or when worn normally, only for convenience of describing the present utility model and simplifying the description, but do not indicate or imply that the device or element to be referred must have a specific azimuth, be configured and operated in a specific azimuth, and should not be construed as limiting the specific protection scope of the present utility model.

A modularized micro unmanned aerial vehicle with stable hovering comprises a frame 10, four rotating mechanisms 20, a picture-transmission camera module 30, a flight control main board 40, a division board 50, a battery assembly 60, an optical flow sensor 70 and a laser sensor 80.

The optical flow sensor 70 and the laser sensor 80 are used for increasing the stability and safety of hovering flight of the unmanned aerial vehicle; the four rotating mechanisms 20, the battery assembly 60, the image capturing module 30, the sub-board 50, the optical flow sensor 70 and the laser sensor 80 are all electrically connected to the flight control main board 40, wherein the optical flow sensor 70 and the laser sensor 80 are mounted on the sub-board 50 and are electrically connected to the flight control main board 40 through pin headers.

The frame 10 comprises a frame main body 11 and a fixing plate 12, the frame main body 11 is of an integral injection molding structure, and a first setting position 13 for installing the image transmission camera module 30, a second setting position 14 for installing and positioning the battery assembly 60, a third setting position 15 for installing the four rotating mechanisms 20 and a fourth setting position 16 for installing and positioning the flight control main board 40 are respectively arranged on the frame main body 11; the first, second, third and fourth setting bits 13, 14, 15 and 16 are connected to each other; the first positioning point 13 and the second positioning point 14 are positioned on the upper end surface of the frame main body 11, wherein the first positioning point 13 is concavely arranged from the upper end of the frame main body 11; the fourth setting position 16 is concavely arranged from the lower end surface of the frame main body 11 and is arranged back to the second setting position 14; preferably, the first positioning portion 13 is provided with a first abutting portion 131, preferably, the second positioning portion 14 is provided with two clamping grooves 141, and preferably, the fourth positioning portion 16 is provided with a plurality of first connecting columns 161 and a plurality of second connecting columns 162, respectively.

Preferably, the frame main body 11 is further provided with a plurality of extension arms 17, one ends of the plurality of extension arms 17 are respectively connected to one ends of the first setting position 13, the second setting position 14 and the third setting position 15, and the plurality of extension arms 17 are in a hollow triangle shape. Under the condition that the carbon plate structural member is not used, the requirements of the installation flatness and the installation strength of the motor 21 are met, the flight stability of the micro unmanned aerial vehicle is ensured, and the requirements of the appearance of the whole machine are met. Such a design both achieves functionality and places emphasis on aesthetics.

Preferably, the extension arms 17 have wire passing grooves 171 for routing wires, and wire passing holes 172 are formed in the side walls of the wire passing grooves 171. The motor 21 wire is conveniently inserted into the machine body and connected with the flight control main board 40, so that the motor 21 wire is effectively protected by the design, and the use safety of the unmanned aerial vehicle is improved.

The four rotating mechanisms 20 are inversely installed in the third installation position 15; the rotating mechanism 20 comprises a motor 21 and a blade 22 connected to the bottom of the motor 21, and the blade 22 is flip-chip mounted in the third mounting position 15.

The image transmission and pickup module 30 is arranged in the first setting position 13; the image transmission camera module 30 comprises a camera 31, an image transmission board 32 and a bracket 33, wherein the camera 31 is arranged on the bracket 33, one end of the camera 31 is electrically connected with the image transmission board 32 through a 3PIN row PIN 34, and the image transmission board 32 is electrically connected with the flight control main board 40. The 3PIN row needles 34 are used for connection, so that the problem of concentrated temperature rise is effectively avoided, and the installation and the disassembly are more convenient. The image transmission camera module has an image transmission function, and is convenient for subsequent data export through signal transmission.

Correspondingly, a second docking portion 331 is disposed on the bracket 33 corresponding to the first docking portion 131, and the bracket 33 is fixedly disposed in the first positioning portion 13 by passing through the first docking portion 131 and the second docking portion 331 through first screws.

The flight control main board 40 is locked in the fourth setting bit 16 through the fixing board 12. Correspondingly, a first connecting hole 41 is formed in the flight control main board 40 corresponding to the first connecting column 161, a second connecting hole 121 is formed in the fixed board 12 corresponding to the second connecting column 162, the flight control main board 40 is mounted in the fourth mounting position 16, the first connecting hole 41 is adapted to the first connecting column 161, and the fixed board 12 is locked to the bottom end surface of the rack main body 11 by passing through the second connecting hole 121 and the second connecting column 162 through second screws.

The battery assembly 60 is mounted within the second mounting location 14; correspondingly, the battery assembly 60 comprises a battery 61 and a mounting rack 62, the battery 61 is mounted in the mounting rack 62, two clamping portions 621 adapted to the two clamping grooves 141 are arranged on the outer periphery side of the mounting rack 62, the battery assembly 60 is mounted in the second mounting position 14, and the two clamping portions 621 are buckled in the two clamping grooves 141. The battery assembly 60 is designed into the second placement site 14, freeing up more space at the bottom. The space can be used for arranging different sensors, expanding the application diversification of the micro unmanned aerial vehicle, and can also be used for various parameter adjustment and interface setting, thereby facilitating the operations of complete machine debugging, function definition and the like.

The utility model mainly adopts the structural design among a frame, four rotating mechanisms, a picture transmission camera module, a flight control main board, a split board, a battery assembly, an optical flow sensor and a laser sensor, adopts an integral injection molding frame main body to realize the inversion of the whole machine, is convenient for installing all parts, lightens the whole weight and fully utilizes the limited space;

The foregoing description is only a preferred embodiment of the present utility model, and is not intended to limit the technical scope of the present utility model, so any minor modifications, equivalent changes and modifications made to the above embodiments according to the technical principles of the present utility model are still within the scope of the technical solutions of the present utility model.

Claims

1. A modular micro-unmanned aerial vehicle with hover stabilization, characterized in that: the unmanned aerial vehicle hovering system comprises a frame, four rotating mechanisms, a picture transmission camera module, a flight control main board, a division board, a battery assembly, an optical flow sensor and a laser sensor, wherein the optical flow sensor and the laser sensor are used for improving the stability and safety of the unmanned aerial vehicle hovering flight; the four rotating mechanisms, the battery assembly, the image transmission and shooting module, the sub-board, the optical flow sensor and the laser sensor are all electrically connected to the flight control main board, wherein the optical flow sensor and the laser sensor are arranged on the sub-board and are electrically connected to the flight control main board through a pin header;

2. The hover-stable modular micro-unmanned aerial vehicle of claim 1, wherein: the image transmission camera module comprises a camera, an image transmission plate and a support, wherein the camera is arranged on the support, one end of the camera is electrically connected with the image transmission plate through a 3PIN row PIN, and the image transmission plate is electrically connected with the flight control main plate.

3. A hover-stable modular micro-unmanned aerial vehicle as recited in claim 2, wherein: the first butt joint portion is arranged in the first positioning position, correspondingly, the second butt joint portion is arranged on the support corresponding to the first butt joint portion, and the support penetrates through the first butt joint portion and the second butt joint portion respectively through first screws to be fixedly arranged in the first positioning position.

4. The hover-stable modular micro-unmanned aerial vehicle of claim 1, wherein: the battery assembly comprises a battery and a mounting frame, wherein the battery is arranged in the mounting frame, two clamping parts which are used for being matched with the two clamping grooves are arranged on the periphery side of the mounting frame, the battery assembly is arranged in the second mounting position, and the two clamping parts are buckled in the two clamping grooves.

5. The hover-stable modular micro-unmanned aerial vehicle of claim 1, wherein: the novel intelligent control device comprises a frame body, a fixing plate, a first connecting column, a second connecting column, a first connecting hole, a second connecting hole, a first connecting hole and a second connecting hole are arranged in a fourth arranging position, a plurality of first connecting columns and a plurality of second connecting columns are respectively arranged in the fourth arranging position, correspondingly, the first connecting hole is formed in the position, corresponding to the first connecting column, of the flight control main plate, the second connecting hole and the second connecting column are respectively penetrated through a second screw by the fixing plate, and the bottom end face of the frame body is locked by the fixing plate.

6. The hover-stable modular micro-unmanned aerial vehicle of claim 1, wherein: the rack is characterized in that a plurality of extension arms are further arranged on the rack main body, one ends of the extension arms are respectively connected with one ends of a first setting position, a second setting position and a third setting position, and the extension arms are in a hollow triangular shape.

7. The hover-stable modular micro-unmanned aerial vehicle of claim 6, wherein: the extension arms are provided with wire passing grooves for wiring, and wire passing holes are formed in the side walls of the wire passing grooves.

8. The hover-stable modular micro-unmanned aerial vehicle of claim 1, wherein: the rotating mechanism comprises a motor and a paddle connected to the bottom of the motor, and the paddle is inversely installed in a third installation position.