CN113511342A

CN113511342A - Electric control device and unmanned aerial vehicle

Info

Publication number: CN113511342A
Application number: CN202110860641.4A
Authority: CN
Inventors: 杨淑侠
Original assignee: Shenzhen Goertek Technology Co ltd
Current assignee: Shenzhen Goertek Technology Co ltd
Priority date: 2021-07-28
Filing date: 2021-07-28
Publication date: 2021-10-19
Anticipated expiration: 2041-07-28
Also published as: CN113511342B

Abstract

The invention discloses an electric control device and an unmanned aerial vehicle, wherein the unmanned aerial vehicle comprises: the device comprises a shell, a first fixing piece and a second fixing piece, wherein an accommodating cavity is formed in the shell; the electric control plate is arranged in the accommodating cavity of the shell; the antenna assembly is arranged on the inner side wall of the shell and/or on the electric control board and is far away from the flying assembly. The invention solves the problems that the wireless antenna is easily influenced by the flight state of the unmanned aerial vehicle, so that the communication effect of the unmanned aerial vehicle in the flight process is poor, the flight control of the unmanned aerial vehicle is influenced, the controllability and the safety of the unmanned aerial vehicle in the flight process are poor, and the unmanned aerial vehicle can be in an out-of-control state even in serious cases.

Description

Electric control device and unmanned aerial vehicle

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to an electric control device and an unmanned aerial vehicle.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle mainly controlled by wireless remote control or self program. Current unmanned aerial vehicle need communicate through wireless antenna and ground control center under the flight condition, however wireless antenna receives unmanned aerial vehicle flight condition's influence very easily, leads to the communication effect of unmanned aerial vehicle flight in-process poor, can make unmanned aerial vehicle be in out of control state even when serious.

Disclosure of Invention

The invention mainly aims to provide an electric control device and an unmanned aerial vehicle, and aims to improve the controllability and safety of the unmanned aerial vehicle.

In order to achieve the above object, the present invention provides an electric control device, including:

the device comprises a shell, a first fixing piece and a second fixing piece, wherein an accommodating cavity is formed in the shell;

the electric control plate is arranged in the accommodating cavity of the shell;

the antenna assembly is arranged on the inner side wall of the shell and/or on the electric control board and is far away from the flying assembly.

Optionally, the drone further comprises an electrical connector;

the antenna assembly and the electric control board are electrically connected through the electric connector.

Optionally, the electrical connector comprises:

the fixed base is fixed on the electric control plate;

and one end of the connecting line joint is fixedly connected with the antenna assembly, and the other end of the connecting line joint is fixed on the fixed base so as to realize the electric connection of the antenna assembly and the fixed base.

Optionally, the electrical connector further comprises:

and the self-locking buckle head is buckled with the fixed base and the wire connecting joint respectively so as to realize that the wire connecting joint is detachably connected to the fixed base.

Optionally, the self-locking buckle head comprises:

the buckle head body is provided with a sliding groove, and a clamping part of the connecting line joint is fixed in the sliding groove;

and the base buckling part is used for clamping and fixing the fixed base.

Optionally, the antenna assembly includes a first antenna unit and a second antenna unit, and the first antenna unit and the second antenna unit are respectively disposed at two ends of the housing and/or the electrical control board in the width direction.

Optionally, the first antenna unit and the second antenna unit are arranged in 180-degree rotational symmetry in the width direction of the unmanned aerial vehicle body.

Optionally, the electronic control device further comprises:

the camera set up in the unmanned aerial vehicle body is kept away from the one end of flight subassembly.

The invention also proposes an unmanned aerial vehicle comprising:

mounting a bracket;

the flying assembly is fixedly arranged at one end of the mounting bracket; and an electrical control device as described above;

the electric control device is arranged at one end, far away from the flying assembly, of the mounting bracket.

Optionally, the flying assembly comprises:

the engine is fixedly arranged at one end of the mounting bracket, which is far away from the antenna component;

a plurality of propellers disposed around the engine.

Optionally, the flying assembly comprises:

a plurality of propellers disposed around the engine.

Optionally, the flying assembly further comprises:

the propeller support frame comprises a plurality of support arms, and each support arm is correspondingly provided with one propeller;

the protective shell is buckled with the propeller support frame; wherein the content of the first and second substances,

the propeller support frame with the middle part of protection casing has still seted up the holding through-hole, the engine passes the holding through-hole is fixed in on the installing support.

The electric control device of the invention arranges the antenna component on the inner side wall of the shell and/or on the electric control board and is arranged far away from the flying component, thus the antenna component and the flying component can be respectively arranged at two ends of the electric control board. The invention can reduce the vibration and electromagnetic induction change generated in the rotation process of the flight assembly, and the influence of a large amount of heat generated by the work of the engine and the propeller on the performance of the antenna, and can ensure the structural stability of the antenna and the high performance and overall reliability of the antenna. The invention solves the problems that the wireless antenna is easily influenced by the flight state of the unmanned aerial vehicle, so that the communication effect of the unmanned aerial vehicle in the flight process is poor, the flight control of the unmanned aerial vehicle is influenced, the controllability and the safety of the unmanned aerial vehicle in the flight process are poor, and the unmanned aerial vehicle can be in an out-of-control state even in serious cases.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

Fig. 1 is a schematic structural view of an electric control device applied to an embodiment of an unmanned aerial vehicle according to the present invention;

fig. 2 is a schematic view of an explosion structure of the electric control device applied to an embodiment of the unmanned aerial vehicle;

FIG. 3 is an internal detail view of an embodiment of the electronic control assembly of the present invention;

FIG. 4 is an internal detail view of another embodiment of the electrical control unit of the present invention;

fig. 5 is a schematic structural diagram of an embodiment of the antenna assembly of fig. 2;

fig. 6 is a schematic structural diagram of another embodiment of the antenna assembly of fig. 2;

FIG. 7 is a schematic diagram of an embodiment of the electrical connector of FIG. 2;

fig. 8 is an exploded view of an embodiment of the electrical connector of fig. 2.

The reference numbers illustrate:

the implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that, if directional indications (such as up, down, left, right, front, and back … …) are involved in the embodiment of the present invention, the directional indications are only used to explain the relative positional relationship between the components, the movement situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indications are changed accordingly.

In addition, if there is a description of "first", "second", etc. in an embodiment of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.

The term "and/or" herein is merely an association describing an associated object, meaning that three relationships may exist, e.g., a and/or B, may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.

The invention provides an electric control device, which is applied to an unmanned aerial vehicle, wherein the unmanned aerial vehicle can be an FPV camera, an aerial camera, a flight control panel, a sensing panel, a holder server and the like.

The unmanned aerial vehicle is an unmanned aerial vehicle mainly controlled by wireless remote control or self program. The existing unmanned aerial vehicle needs to communicate with a ground control center through a wireless antenna in a flight state, receive a control instruction sent by the ground control center, execute tasks such as flight, photographing and the like, and transmit the flight state back to the control center; in addition, during the flight process, the unmanned aerial vehicle also needs to actively or passively change the flight state according to the flight condition to obtain an expected flight track or ensure the safety of the unmanned aerial vehicle. However, wireless antenna receives unmanned aerial vehicle flight state's influence very easily, leads to unmanned aerial vehicle flight in-process communication effect poor, influences unmanned aerial vehicle's flight control, leads to unmanned aerial vehicle flight in-process controllability and security poor, can make unmanned aerial vehicle be in the out of control state even when serious. How to guarantee that the signal is good, not influenced by machine flight again, the antenna is very important at the inside locating position of unmanned aerial vehicle and design form and with mainboard connection's reliability.

In order to solve the above problem, referring to fig. 1 to 8, in an embodiment of the present invention, the electric control device includes:

the shell 110 is provided with an accommodating cavity inside the shell 110;

and an electronic control board 120 disposed in the accommodating cavity of the housing 110, wherein the antenna assembly 300 is disposed on an inner sidewall of the housing 110 and/or on the electronic control board 120.

The antenna assembly 200 is arranged on the inner side wall of the shell 200 and/or on the electric control board 110, and is far away from the flying assembly 300.

In this embodiment, electrically controlled device can be arranged in the flight subassembly work of control unmanned aerial vehicle. The housing 110 includes a front housing 111, a rear housing 112, and an end cap 113, the front housing 111, the rear housing 112, and the end cap 113 enclose an accommodation space for accommodating the electronic control board 120, the antenna assembly 300 may be disposed on an inner wall surface of the housing 110, or may be disposed on the electronic control board 120, when disposed on the inner wall surface of the housing 110, specifically may be disposed on the inner wall surface of the front housing 111 of the housing 110, the antenna assembly 300 may be implemented by using an FPC antenna, the FPC antenna may be adhered to the housing 110 by using a sticky material, or the antenna assembly 300 may be embedded in the housing 110 by using an embedded manner, specifically, after the antenna assembly 300 is routed through a square of a circuit wiring, when the housing 110 is manufactured, the antenna assembly 300 is placed in a mold of the housing 110, so that the antenna assembly 300 is integrally formed in the housing 110. Wherein the housing 110 is made of a non-conductive material, such as silicon oxide, aluminum oxide, FR-4 glass epoxy, in some embodiments, the housing 110 may be made of a material with a buffer to reduce the transmission of the vibration generated by the flying assembly 200 to the antenna assembly 300 disposed on the housing 110, thereby reducing the influence of the flying assembly 200 on the antenna assembly 300. The number of the electric control boards 120 may be multiple, for example, two electric control boards 120 may be disposed on two sides of the mounting bracket 500, and the mounting bracket is provided with support ribs for supporting the electric control boards 120, so as to prevent the electric control boards 120 from directly contacting the support bracket 120, increase the heat dissipation space of the electronic components on the electric control boards 120, and improve the heat dissipation effect of the electric control boards 120.

Automatically controlled board 110 constitutes the unmanned aerial vehicle body with unmanned aerial vehicle body, and unmanned aerial vehicle can realize the aircraft of VTOL, and the fuselage framework is used for supporting, automatically controlled board of fixed mounting and flight subassembly 200, automatically controlled board 120 with flight subassembly 200 electricity is connected, and automatically controlled board is used for controlling flight subassembly 200 work, and flight subassembly 200 then is used for providing power for unmanned aerial vehicle, and unmanned aerial vehicle body 100 can be cylindrical setting, or is the setting of square column form, is the horizontally convention based on ground, when unmanned aerial vehicle is in level and quiescent condition (for example subaerial or on another horizontal surface), unmanned aerial vehicle body 100 is vertical installation, perpendicular to ground promptly. In contrast, when the drone is in a horizontal and stationary state, the horizontally mounted drone body 100 is parallel to the ground. Unmanned aerial vehicle body 100 has top and bottom in its vertical direction, and antenna module 300 and flight subassembly 200 divide the top and the bottom of locating unmanned aerial vehicle body 100, or antenna module 300 is close to the top setting.

The electric control board 110 is accommodated in the fuselage structure of the unmanned aerial vehicle body 100, the electric control board 110 is provided with a wireless receiving/transmitting module, a main controller, and a driver (electronic governor), the wireless communication module can receive a control instruction output by the ground remote control device, for example, the control instruction for controlling the unmanned aerial vehicle to ascend, descend, translate left and right, rotate, hover, etc., and output the received control instruction to the main controller, so that the main controller responds to the control instruction and outputs a control signal to the driver, and the driver controls the flight assembly 200 to operate to execute corresponding actions. The wireless communication module can also transmit the working state of the unmanned aerial vehicle (such as parameters of the flying height, flying speed, flying attitude and the like of the unmanned aerial vehicle) output by the main controller, feedback signals (such as response signals) and the like back to the ground remote control device so as to realize information interaction between the unmanned aerial vehicle and the ground remote control device. When unmanned aerial vehicle had the shooting function, the image data that the shooting subassembly was shot can be exported to main control unit, and main control unit carries out the image processing back, exports wireless communication module again to the image data of will shooing etc. pass back to ground remote control unit, in order to realize the information interaction between unmanned aerial vehicle and the ground remote control unit.

The wireless communication module may be a WIFI, 5G communication module, a radio frequency unit, a WLAN, a GPRS, a bluetooth communication module, etc., and the wireless communication module is electrically connected to the antenna assembly 300, so as to receive a control command sent by the ground remote control device through the antenna assembly 300, or transmit data back to the ground remote control device through the antenna assembly 300. The unmanned aerial vehicle body 100 is integrated with one or more combinations of wireless communication modules such as WIFI, 5G communication module, radio frequency unit, WLAN, GPRS and Bluetooth communication module. Antenna module 300 is according to wireless communication module's difference, and the type and the quantity of setting are also different, for example when being provided with the WIFI module in unmanned aerial vehicle body 100, antenna module 300 then includes the WIFI antenna that can realize WIFI communication, and when unmanned aerial vehicle body 100 was provided with 5G communication module, antenna module 300 then includes the 5G antenna that can realize 5G communication.

When the antenna assembly 300 is disposed on the electronic control board 120, the antenna assembly 300 may be integrally disposed on the wireless communication module, that is, implemented by using an AOP (antenna-on-package) and an AIP (antenna-in-package), and the antenna assembly 300 is sealed by a potting adhesive or disposed on a surface of the wireless communication module and integrally disposed with the wireless communication module. Alternatively, the antenna assembly 300 may be implemented by forming antenna traces on the electronic control board 120 in the form of circuit traces. The antenna may be a bent antenna (planar structure) or a multi-layer antenna, for example, the bent antenna may be an F-shaped, L-shaped, square, circular, spiral, m-shaped, fishbone-shaped, or zigzag antenna, and the bent antenna may be laid on the housing 110 or on the antenna substrate.

It can be understood that, set up antenna module 300 on the internal wall face of unmanned aerial vehicle body 100, with wireless communication module, main control unit etc. set up circuit module branch on automatically controlled board 120 locate two installation carriers on, need not to set up the circuit board separately, under the condition that does not change unmanned aerial vehicle body 100 volume, can reduce the volume of automatically controlled board 120, make things convenient for automatically controlled board 120 to install in unmanned aerial vehicle's casing 110, still be favorable to simplifying the PCB board overall arrangement of automatically controlled board 120 simultaneously. In addition, the antenna assembly 300 and the circuit modules on the electronic control board 120 are arranged in a dispersed manner, so that the influence of electromagnetic radiation generated by switching devices and the like on the electronic control board 120 on the normal operation of the antenna can be avoided, and the reduction of electromagnetic interference between the electronic control board components of the unmanned aerial vehicle is facilitated. The heat generated by the power devices on the electronic control board 120, such as the power supply, inverter, etc., will not affect the operation of the antenna assembly 300. Set up antenna module 300 on the casing, can increase antenna module 300's design space to can avoid the influence of circuit wiring on the automatically controlled board to the antenna, can improve antenna module's interference killing feature, improve antenna module 300's stability.

In practice, the antenna assembly is disposed on the electronic control board and/or the housing, and is disposed as far away from the flying assembly 200 as possible. Unmanned aerial vehicle's flight subassembly 200 includes at least one screw 220 and the engine 210 that drives screw 220 work in to screw 220 and engine 210 all set up in the bottom of unmanned aerial vehicle body 100, and engine 210 can control screw 220, just reversal and rotation angle etc. to make unmanned aerial vehicle rise, descend, control translation, control rotation, hover etc. operation. Screw 220 can produce the vibration at the pivoted in-process, and the motor also can produce the electromagnetic induction change at the course of the work, simultaneously at engine 210, screw 220 during operation, also can produce a large amount of heats, and antenna module 300 carries out data transmission through the mode of electromagnetic wave at the in-process of work, and the vibration of unmanned aerial vehicle during operation, electromagnetic induction and the parameter variation that factors such as generate heat all can influence the antenna, and then influence the performance of antenna. For this reason, this embodiment sets up flight subassembly 200 in the bottom of unmanned aerial vehicle body 100, antenna module 300 then sets up in the top of unmanned aerial vehicle body 100, so that receive/send wireless communication information, thereby make antenna module 300 and flight subassembly 200 both keep away from as far as when the installation, in order to guarantee that the antenna can adapt to unmanned helicopter's operating condition, do not receive the interference of unmanned helicopter flight state, do not influence unmanned aerial vehicle's antenna performance, guarantee to carry out reliable communication between ground remote control unit and the unmanned aerial vehicle, improve unmanned aerial vehicle's controllability and security.

The electronic control device of the present invention arranges the antenna assembly 300 on the inner sidewall of the housing 110 and/or on the electronic control board 120, and is arranged away from the flying assembly 300, so that the antenna assembly 300 and the flying assembly 200 can be arranged at two ends of the electronic control board 110. The invention can reduce the vibration and electromagnetic induction change generated in the rotation process of the flight assembly 200 and the influence of a large amount of heat generated by the work of the engine 210 and the propeller 220 on the antenna performance, can ensure the stability of the antenna structure and has high antenna performance and overall reliability. The invention solves the problems that the wireless antenna is easily influenced by the flight state of the unmanned aerial vehicle, so that the communication effect of the unmanned aerial vehicle in the flight process is poor, the flight control of the unmanned aerial vehicle is influenced, the controllability and the safety of the unmanned aerial vehicle in the flight process are poor, and the unmanned aerial vehicle can be in an out-of-control state even in serious cases.

Referring to fig. 2 or 3, in an embodiment, when the antenna assembly 300 is disposed on the inner sidewall of the housing 110, the drone further includes an electrical connector 400;

the antenna assembly 300 and the electronic control board 120 are electrically connected by the electrical connector 400.

In this embodiment, the wireless communication module, the main controller, and the like are disposed on the electronic control board 120, and an antenna feeding point are disposed on the electronic control board 120, when the antenna assembly 300 is disposed on the inner sidewall of the housing 110, the antenna assembly 300 and the wireless communication module on the electronic control board 120 are electrically connected by using the electrical connector 400, so that the antenna assembly 300 is electrically connected to the antenna feeding point and the antenna feeding point disposed on the electronic control board 120, respectively, to form a feeding loop, so that the wireless communication module transmits data to the antenna assembly 300 through the antenna feeding point and the antenna feeding point, or receives data from the antenna assembly 300. The electrical connector 400 may be a cable 420, an FPC, or the like, one end of the electrical connector 400 may be soldered to the antenna unit of the antenna assembly 300, the other end of the electrical connector 400 may be electrically connected to a terminal provided on the electronic control board 120, or one end of the electrical connector 400 may be soldered to the electronic control board 120 by a soldering method.

Referring to fig. 2, 3, 7 and 8, in one embodiment, the electrical connector 400 includes:

a fixing base 410 fixed on the electric control board 110;

one end of the connection joint 420 is fixedly connected to the antenna assembly 200, and the other end of the connection joint 420 is fixed to the fixing base 410, so as to electrically connect the antenna assembly 200 and the fixing base 410.

In this embodiment, the fixing base 410 is fixed on the electronic control board 110 by welding, one end of the connection joint 420 is electrically connected to the antenna unit of the antenna assembly 300, and the connection joint can be fastened to the fixing base 410 disposed on the electronic control board 120 by fastening, inserting, or the like. The antenna assembly 300 and the electronic control board 120 are detachably and fixedly electrically connected through the fixing base 410 and the connecting line joint 420, which is beneficial to solving the problem of antenna contact caused by flight vibration, so that the problem that the antenna assembly 300 and the electronic control board 120 are electrically disconnected due to relative motion when the unmanned aerial vehicle generates vibration and impact in flight, and a wireless communication module on the electronic control board 120 cannot send/receive communication signals. Optionally, a clamping groove 110a is further formed in the housing 110 of the drone body 100, and the cable 420 connecting the electronic control board 120 and the antenna assembly 300 can be fixed to the clamping groove in the fuselage front shell 111, so that the mounting is facilitated, friction between the cable and the electronic control board 120 and/or the housing 110 is avoided, and the cable 420 can be protected.

Referring to fig. 7 and 8, further, in order to further improve the stability between the fixed base 410 and the connection terminal 420, a self-locking buckle 430 is further provided in this embodiment, and the self-locking buckle 430 is respectively buckled with the fixed base 410 and the connection terminal 420, so as to detachably connect the connection terminal 420 to the fixed base 410, and buckle the terminal and the base by the self-locking buckle 430, so that the terminal and the base do not fall off when falling and using. Specifically, the self-locking buckle head 430 is provided with a buckle head body 431, and the buckle head body 431 is provided with a sliding groove for fixing the clamping part 421 of the connecting line joint 420 in the sliding groove; the self-locking buckle head 430 is further provided with a base buckling part 432 for the fixing base 410 to be clamped and fixed.

Two sides of the button head body 431 extend towards the direction of the fixing base 410, and the two sides are bent inwards and oppositely to form folded edges, and the two folded edges form a sliding groove for the clamping portion 421 of the connecting line joint 420 to slide into. The base engaging portion 432 is U-shaped, and a buckle is further disposed on the fixing base 410 in a protruding manner, so that the base engaging portion 432 can be fixed on the fixing base 410 when the base engaging portion 432 is fastened to the fixing base 410.

The connecting wire joint 420 can be fixed on the self-locking buckle head 430 through the sliding groove in the buckle head body 431, and the base buckling part 432 of the self-locking buckle head 430 is clamped on the fixed base 410. Thus, under the clamping action of the self-locking buckle head 430, the relative movement between the fixed base 410 and the connection joint 420 in the falling and using processes can be prevented, so that the connection joint 420 falls off from the fixed base 410, and the relative movement between the antenna assembly and the electronic control board can be prevented. In the assembling process of the electric control device, after the fixing base 410 is fixed on the electric control board 110, the connection line joint 420 is locked on the fixing base 410, and then the joint and the base are buckled by the self-locking buckle head 430, so that the fixing connection between the fixing base 410 and the connection line joint 420 is realized.

Referring to fig. 2 to 4, in an embodiment, the antenna assembly 300 includes a first antenna unit 310 and a second antenna unit 320, and the first antenna unit 310 and the second antenna unit 320 are respectively disposed at two ends of the electrical control board 120 and/or the housing 110 in the width direction.

In this embodiment, the first antenna unit 310 and the second antenna unit 320 may be respectively disposed at two edges of the inner surface of the housing 110 in the width direction, and the first antenna unit 310 and the second antenna unit 320 may also be respectively disposed at two edges of the electrical control board 120 in the width direction. In the first antenna unit 310 and the second antenna unit 320, either one of the antenna units may be configured to receive a communication signal (such as a control command) sent by the ground remote control device, and the other antenna unit may be configured to send a communication signal (such as image data, an operating parameter, a state, and the like of the drone) to the ground remote control device. Specifically, the first antenna unit 310 may be a receiving antenna and the second antenna may be a transmitting antenna, or the first antenna unit 310 may be a transmitting antenna and the second antenna unit 320 may be a receiving antenna. When the antenna assembly 300 includes a WIFI antenna, the first antenna unit 310 and the second antenna unit 320 may operate in different WIFI frequency bands, for example, the first antenna unit 310 operates in one WIFI frequency band, and the second antenna unit 320 operates in another WIFI frequency band. Referring to fig. 5 and 6, the first antenna element 310 is provided with an antenna body 311, an antenna feeding point 312, and an antenna grounding point 313, and the antenna feeding point 312 and the antenna grounding point 313 are electrically connected to the electronic control board 110 through the electrical connector 400. The second antenna unit 320 is provided with an antenna body 321, an antenna feeding point 322, and an antenna grounding point 323, and the antenna feeding point 322 and the antenna grounding point 323 are electrically connected to the electronic control board 110 through the electrical connector 400.

It should be noted that, unmanned aerial vehicle electronic product at present stage is popularized gradually in people's life, also is higher and higher to the requirement of the ID of product, function, structure, performance design, and this kind of product all has dual-frenquency two WIFI antennas, and two WIFI antennas require higher to the isolation of antenna, promote antenna isolation through change antenna form, feed point ground connection position usually, however the effect is relatively poor, influences the reliable communication between unmanned aerial vehicle and the ground easily.

For this reason, referring to fig. 2 to 4, in an embodiment, the first antenna unit 310 and the second antenna unit 320 are disposed in a 180-degree rotational symmetry manner in the width direction of the drone body 100.

In this embodiment, the first antenna unit 310 and the second antenna unit 320 have the same structure, and two edges of the two antenna units in the width direction of the inner surface of the housing 110 are arranged in a 180-degree rotational symmetry manner, or two edges of the two antenna units in the width direction of the electric control board 120 are arranged in a 180-degree rotational symmetry manner, so that the symmetry of the antenna can be ensured by the dual design of the symmetry and the electrical symmetry of the structure, and the isolation performance of multiple antennas can be improved by the orthogonal directivity of the two antennas.

Referring to fig. 2 or 3, in an embodiment, the electric control device further includes:

the camera 600 is disposed at one end of the electric control board 120 far away from the flying assembly 200.

Optionally, the unmanned aerial vehicle may be provided with a camera 600 to implement high altitude aerial photography, and the unmanned aerial vehicle body 100 further includes a Graphics Processing Unit (GPU) and a memory, where the Graphics Processing Unit processes image data of a still picture or a video obtained by the camera 600 in the video capture mode or the image capture mode. The image frames processed by the graphic processor can be stored in a vast amount of personal memories (or other storage media) or transmitted to a ground remote control device, a mobile terminal, etc. via a radio frequency unit or a WiFi module. Specifically, after receiving a flight control command and a shooting control command sent by the ground remote control terminal, the flight control terminal performs flight operations such as ascending, descending, hovering and the like according to the flight control command, shoots according to the shooting control command, and simultaneously adjusts the flight attitude to adjust the shooting angle.

The propeller 220 can vibrate in the rotating process, which may affect the image imaging effect of the static pictures or videos when the camera 600 works at the same time as the video and suitcase, and meanwhile, the camera 600 can generate a large amount of heat when working, and a large amount of heat can also be generated when the engine 210 and the propeller 220 work. For this reason, this embodiment locates the top and the bottom of unmanned aerial vehicle body 100 with camera 600 and flight subassembly 200 branch, or camera 600 is close to the top and sets up. In addition, camera 600 and flight subassembly 200 divide and locate the both ends of unmanned aerial vehicle body 100, can increase the spatial distance between the two, are favorable to dispersing the heat source of unmanned aerial vehicle body 100, can also increase heat radiating area between two high-power devices, are favorable to improving unmanned aerial vehicle's radiating efficiency.

In a specific embodiment, the number of the cameras 600 may be two, two cameras 600 are sequentially arranged in the length direction of the drone body 100, and the cameras 600 and the antenna assembly 300 may be arranged side by side in the horizontal direction, and when the antenna assembly 300 includes the first antenna unit 310 and the second antenna unit 320, the two antenna units are respectively arranged on two sides of the camera 600. So arranged, the antenna assembly 300 and camera head 600 may be spatially located as far apart as possible from the flying assembly 200.

Referring to fig. 2, in an embodiment, the drone body 100 further includes:

a mounting bracket 500, on which the flying assembly 200, the housing 110 and the electronic control board 120 are respectively mounted.

In this embodiment, installing support 500 is as unmanned aerial vehicle's fuselage center, can fix on installing support 500 through screw, detachable such as buckle between automatically controlled board 120 and the installing support 500, still be provided with the buckling parts on installing support 500, preceding shell 111 and the back shell 112 of casing 110 can pass through the buckling parts lock of buckle and installing support 500 to encapsulate automatically controlled board, antenna module 300 etc. in casing 110, in order to prevent rainwater, sand and dust etc. from getting into casing 110, influence the normal work of automatically controlled board and antenna module 300. The flying assembly 200 is arranged at the bottom of the fixed support, and the flying assembly 200 and the fixed support can be fixedly connected through screws, buckles and the like. In an embodiment, the electric control board 120 and the position corresponding to the electric control board 120 are both provided with screw holes, and the front shell 111 of the housing 110, the electric control board 120 and the mounting bracket 500 are fixedly connected by passing through the screw holes through screws.

When the antenna assembly 300 is mounted on the housing 110 and/or the electronic control board 120, the housing 110 and the electronic control board 120 are fixed to the flying assembly 200 through the mounting bracket 500, that is, the housing 110 and the electronic control board 120 do not directly contact with the flying assembly 200, so that the vibration and heat transmission of the flying assembly 200 are reduced at the interval of the mounting bracket 500, and thus, the influence of the vibration on the antenna assembly 300 by the flying assembly 200 can be further reduced.

Referring to fig. 2, in one embodiment, the flying assembly 200 includes:

a motor 210 fixedly disposed at an end of the mounting bracket 500 remote from the antenna assembly 300;

and a plurality of propellers 220 disposed around the engine 210.

In this embodiment, unmanned aerial vehicle's flight subassembly 200 adopts pure electric drive, and engine 210 is the motor promptly, and unmanned aerial vehicle still includes the battery, provides the electric energy for the operation of motor through the battery, and the motor further drives screw 220 and rotates to realize unmanned aerial vehicle's flight. The weight of battery accounts for unmanned aerial vehicle weight's proportion is great, in order to realize unmanned aerial vehicle's balance, can set up the battery on installing support 500, for example set up the battery in installing support 500's bottom, specifically can set up between installing support 500's bottom and motor support. Alternatively, it may be mounted on the side of the mounting bracket 500 away from the electronic control board 120.

Unmanned aerial vehicle's flight subassembly 200 can also adopt the oil to move the drive, and engine 210 provides power for unmanned aerial vehicle through using the fuel, and unmanned aerial vehicle still includes the oil tank, and engine 210 further drives screw 220 and rotates to realize unmanned aerial vehicle's flight. The oil tank may be disposed on the mounting bracket 500, for example, the oil tank may be disposed at the bottom of the mounting bracket 500, and may be disposed between the bottom of the mounting bracket 500 and the motor bracket.

The engine 210 may be fixedly mounted on the mounting bracket 500 by screws, fasteners, etc., and the engine 210 and the electronic control board 120 may be electrically connected by an electrical connector in a pluggable manner.

Propellers 220 include two or more, such as four, six, eight, etc., each propeller 220 including at least one rotor. Each propeller 220 may also include a pair of rotors facing each other. Of course in other embodiments, propeller 220 may include more than two rotors. The propeller 220 may be made of a non-conductive material, such as plastic, carbon fiber. When the drone is in operation, each propeller 220 rotates about an axis of rotation. Unmanned aerial vehicle helicopter can be realized to each screw 220, can change lift through the rotational speed that changes each screw 220, and then changes unmanned aerial vehicle's gesture and position. Each screw 220 is the symmetry and sets up, and the direction of rotation of two screw 220 of symmetry setting can set up to opposite to offset the rotatory produced moment of single screw 220 each other, adjust the rotational speed of each screw 220, just can adjust unmanned aerial vehicle's flight gesture and speed.

Referring to fig. 2, in one embodiment, the flying assembly 200 further comprises:

the propeller support frame 230, the propeller support frame 230 includes a plurality of support arms 231, and each support arm 231 is correspondingly provided with one propeller 220;

a protective housing 240 fastened to the propeller support frame 230; wherein the content of the first and second substances,

the middle portions of the propeller support frame 230 and the protective casing 240 are further provided with accommodating through holes, and the engine 210 is fixed on the mounting bracket 500 through the accommodating through holes.

In this embodiment, the propeller support frame 230 is disposed in an annular shape, the annular support includes an inner ring frame and an outer ring frame, the arc-shaped propeller support frame 230 is formed between the inner ring frame and the outer ring frame of the propeller support frame 230 and the support arms 231, and the engine 210 is installed in the middle of the propeller support frame 230 and the protective casing 240 to form the arc-shaped propeller support frame 230

Support arm 231 uses engine 210 as the center, to extending all around, and connect in inner ring frame and outer loop frame, can the symmetry set up between each support arm 231, be provided with a plurality of strengthening ribs between every support arm 231 and the ring carrier, can fix two adjacent support arms 231 through the strengthening rib, so that improve the stability when flying subassembly 200 rotates, prevent that the great flight subassembly 200 that leads to of resistance of wind receives the damage when owing to rotating, can improve the intensity of screw 220 through the strengthening rib. The propeller 220 may be disposed at the end of the support arm 231, and the engine 210 drives the propeller 220 to rotate through the support arm 231.

The protective shell 240 is buckled with the propeller support frame 230, the propeller 220 is accommodated in the protective shell, the propeller 220 is surrounded, the propeller 220 can be prevented from being out of control and colliding with objects in the flying process, and the phenomenon that the propeller 220 causes great harm to the airplane and personal safety when the unmanned aerial vehicle falls from high altitude or collides at high speed can be avoided. The protective housing 240 and the propeller support frame 230 may be made of a light material such as plastic to reduce the weight of the unmanned aerial vehicle. In order to not affect the heat dissipation of the propeller 220, enhance the shielding performance of the protective cover of the propeller 220 and improve the protection of the human body, the protective casing 240 may be disposed in a grid. Protection casing 240 sets up in the lower part of unmanned aerial vehicle body 100, can support the unmanned aerial vehicle organism, also can support subaerial undercarriage when can stopping as unmanned aerial vehicle.

It can be understood that, the installing support 500 of the unmanned aerial vehicle body 100 is arranged in the middle of the unmanned aerial vehicle, the propeller 220 is arranged in the horizontal direction on the peripheral side of the propeller support frame 230, the antenna assembly 300 is arranged on the unmanned aerial vehicle body 100 in the vertical direction, the antenna assembly 300 and the propeller 220 are fixed through the supporting support respectively, the propeller 220 is arranged at the tail end of the horizontal direction, and the antenna assembly 300 is arranged at the tail end of the vertical direction of the unmanned aerial vehicle. So set up, be favorable to realizing unmanned aerial vehicle's gravity balance, guarantee unmanned aerial vehicle operation's reliability, simultaneously can be on spatial position, increase spatial distance between the two, thereby make antenna module 300 and screw 220 both keep away from as far as when the installation, in order to guarantee that the antenna can adapt to unmanned helicopter's operating condition, do not receive screw 220 flight state's interference, do not influence unmanned aerial vehicle's antenna performance.

The above description is only an alternative embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims

1. The utility model provides an electrically controlled device, is applied to in the unmanned aerial vehicle, unmanned aerial vehicle includes the flight subassembly, its characterized in that, electrically controlled device includes:

the antenna assembly is arranged on the inner side wall and/or the electric control board and is far away from the flying assembly.

2. The electrical control device of claim 1, wherein the drone further comprises an electrical connector;

3. The electrical control device of claim 2, wherein the electrical connector comprises:

the fixed base is fixed on the electric control plate;

4. The electrical control device of claim 3, wherein the electrical connector further comprises:

5. The electrical control device of claim 4, wherein the self-locking button head comprises:

and the base buckling part is used for clamping and fixing the fixed base.

6. The electric control device according to any one of claims 1 to 5, wherein when the antenna assembly is disposed on an inner side wall of the housing, the antenna assembly includes a first antenna unit and a second antenna unit, the first antenna unit and the second antenna unit being disposed at both ends in a width direction of the housing;

when the antenna assembly is arranged on the electric control board, the first antenna unit and the second antenna unit are respectively arranged at two ends of the electric control board in the width direction.

7. The electric control device according to claim 6, wherein the first antenna unit and the second antenna unit are arranged in 180-degree rotational symmetry in the housing width direction.

8. The drone of claim 6, wherein the electrical control device comprises:

the camera is arranged on the electric control plate and is far away from one end of the flying assembly.

9. A drone, characterized in that it comprises:

mounting a bracket;

the flying assembly is fixedly arranged at one end of the mounting bracket; and an electric control device according to any one of claims 1 to 8;

10. The drone of claim 9, wherein the flight assembly comprises:

a plurality of propellers disposed around the engine.