CN209946662U

CN209946662U - Unmanned aerial vehicle flies accuse ware

Info

Publication number: CN209946662U
Application number: CN201920676711.9U
Authority: CN
Inventors: 杨晓晶
Original assignee: Xi'an Emperor And Electronic Technology Co Ltd
Current assignee: Xi'an Emperor And Electronic Technology Co Ltd
Priority date: 2019-05-13
Filing date: 2019-05-13
Publication date: 2020-01-14
Anticipated expiration: 2029-05-13

Abstract

The application discloses an unmanned aerial vehicle flight controller, and belongs to the technical field of unmanned aerial vehicle control; an unmanned aerial vehicle flight controller comprises a flight controller shell consisting of an upper cover plate, a lower cover plate and a shell, wherein a flight control plate is fixed on the lower cover plate through a lower bottom shell, and one end of the shell is respectively provided with a power supply interface, a signal aviation plug and an antenna interface; the flight control panel comprises a power supply module, a wireless communication module, a CPU chip and an FPGA chip which are connected through an EMIF bus, wherein the power supply module is connected with a power supply interface, and external equipment of the flight control device is connected with the FPGA chip through a signal aerial plug; the wireless communication module is respectively connected with the CPU chip and the antenna interface, the utility model adopts the fixed connection of the shell and the lower shell to protect the internal flight control panel, simplify the hardware structure and further reduce the volume; a plurality of peripheral interfaces are configured in the peripheral installation area at the left end of the shell, flexible configuration can be achieved according to different requirements, and interface expansion design is not needed.

Description

Unmanned aerial vehicle flies accuse ware

Technical Field

The invention relates to the technical field of unmanned aerial vehicle control, in particular to a flight controller of an unmanned aerial vehicle.

Background

In the field of unmanned aerial vehicles, how to realize better unmanned aerial vehicle control is always a difficult problem. The hardware structure of the unmanned aerial vehicle controller in the prior art is complex, the remote control instruction group delay condition is long, meanwhile, the problem that peripheral equipment needs an interface chip is difficult to solve, especially the problem that the peripheral equipment needs the interface chip is difficult to overcome, the expansibility is poor, and the requirement in the current unmanned aerial vehicle control field cannot be met.

Disclosure of Invention

In view of the problems of large size, high time delay and many interfaces of an unmanned aerial vehicle control system in the prior art, the hardware structure of the unmanned aerial vehicle controller is simplified, the interfaces are simplified, and the unmanned aerial vehicle flight controller is provided.

An unmanned aerial vehicle flight controller comprises a flight controller shell consisting of an upper cover plate, a lower cover plate and a shell, wherein a flight control plate is fixed on the lower cover plate through a lower bottom shell, and one end of the shell is respectively provided with a power supply interface, a signal aviation plug and an antenna interface; the flight control board comprises a power supply module, a wireless communication module, a CPU chip and an FPGA chip which are connected through an EMIF bus, wherein the power supply module is connected with a power supply interface and respectively supplies power to the CPU chip and the FPGA chip; the external equipment of the flight controller is connected with the FPGA chip through a signal aerial plug; the wireless communication module is respectively connected with the CPU chip and the antenna interface.

Further, the signal aerial plug comprises RS232, RS422, CAN, PWM, GPIO, ADC and DAC interfaces.

Furthermore, the external device of the flight controller sends information to the FPGA chip through signal aerial plug, and the FPGA chip sends the information to the CPU chip; and a control instruction sent by the CPU chip is sent to the external equipment of the flight controller through the FPGA chip and the signal aerial plug.

Furthermore, the antenna interface is also connected with a wireless antenna, and the CPU chip is in wireless communication with the control source through the wireless communication module and the wireless antenna.

Furthermore, one surface of the upper cover plate, which is buckled with the shell, is provided with a rectangular boss fixed with the flight control plate, and the other surface is provided with a heat dissipation plate.

Further, at least one screw hole is arranged on the other surface of the upper cover plate.

Furthermore, one surface of the lower cover plate buckled with the shell is provided with a step-shaped boss fixed with the lower cover plate, and the other surface is provided with a heat dissipation plate.

Further, at least one screw hole is arranged on the other surface of the lower cover plate.

Furthermore, a weight reduction groove is formed in the shell.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model adopts the fixed connection between the shell and the lower shell, and protects the inner unmanned plane flight control board by the way of the mutual buckling of the upper cover plate and the lower cover plate, thereby simplifying the hardware structure of the unmanned plane controller and further reducing the volume of the hardware structure; the peripheral installation area at the left end of the shell is provided with a plurality of peripheral interfaces, so that flexible configuration can be realized according to different requirements, and interface expansion design is not needed; the flight control computer adopts two chips of a CPU and an FPGA to be integrated on a flight control board, the requirements of the flight control system on control capability and operation capability CAN be simultaneously met, and the signal aerial plug CAN integrate various interfaces such as RS232, RS422, CAN, PWM, GPIO, ADC, DAC and the like.

Drawings

Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:

fig. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a front view of the upper cover plate of the present invention;

fig. 3 is a rear view structure diagram of the upper cover plate of the present invention;

fig. 4 is a rear view structure diagram of the lower cover plate of the present invention;

FIG. 5 is a front view of the lower cover plate of the present invention;

fig. 6 is a schematic connection diagram of the flight control board circuit module according to the present invention;

fig. 7 is a schematic diagram of module connection between the CPU and the FPGA of the present invention.

In the figure: 1-upper cover plate; 2-flight control panel; 3-a shell; 4-a lower bottom shell; 5-lower cover plate; 6-an antenna interface; 7-signal aerial plug; 8-power interface.

Detailed Description

The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

Referring to fig. 1-6, an unmanned aerial vehicle flight controller comprises a shell 3, wherein the shell 3 is preferably rectangular, a lower bottom shell 4 is fixedly connected with the shell 3, the lower bottom shell 4 is a rectangular plate and has a flat surface, a flight control panel 2 is placed on the lower bottom shell 4, and the lower bottom shell 4 and the flight control panel 2 can be fixed with each other through screws or bolts, so that the flight control panel 2 can be ensured to be arranged inside the shell 3 and fixed on the lower bottom shell 4, the flight control panel 2 is protected from shaking back and forth, and the flight control panel 2 is not damaged; meanwhile, in order to further increase the protection force, an upper cover plate 1 and a lower cover plate 5 are respectively arranged at the upper end and the lower end of the shell 3, the upper cover plate 1 and the lower cover plate 5 can be mutually buckled with the shell 3, so that the outer protection of the flight control panel 2 is completed, and the size of the hardware structure of the unmanned aerial vehicle controller is further reduced by simplifying the hardware structure; the left end of the shell 3 is provided with a peripheral installation area, the peripheral installation area is provided with a power interface 8, and two sides of the power interface 8 are respectively provided with an antenna interface 6 and a signal aerial plug 7; a plurality of peripheral interfaces are configured in the peripheral installation area at the left end of the shell, flexible configuration can be achieved according to different requirements, and interface expansion design is not needed.

The flight control panel 2 comprises a power supply module, a wireless communication module, a CPU chip and an FPGA chip which are connected through an EMIF bus, wherein the power supply module is connected with the power supply interface 8 and respectively supplies power to the CPU chip and the FPGA chip; the external equipment of the flight controller is connected with the FPGA chip through a signal aviation plug 7; the wireless communication module is respectively connected with the CPU chip and the antenna interface 6, the flight control computer adopts two chips of the CPU and the FPGA to be integrated on a flight control board, the requirements of the flight control system on the control capability and the operation capability CAN be simultaneously met, and the external interface of the flight control computer supports various interfaces such as RS232, RS422, CAN, PWM, GPIO, ADC, DAC and the like.

The external equipment of the flight controller sends information to the FPGA chip through the signal aviation plug 7, and the FPGA chip sends the information to the CPU chip; the control instruction that the CPU chip sent sends is sent to flying accuse ware external device through FPGA chip, signal aviation plug 7, and antenna interface 6 still is connected with wireless antenna, and the CPU chip carries out wireless communication through wireless communication module, wireless antenna and control source.

Referring to FIGS. 2-3; one surface of the upper cover plate 1, which is buckled with the shell 3, is provided with a rectangular boss fixed with the flight control panel 2, the rectangular boss is at least one layer, preferably two layers, one layer is used for extending downwards to be contacted with the flight control panel 2, and the other layer is mainly used for installing the flight control panel 2; the other side of the upper cover plate 1 is provided with a heat dissipation plate, so that heat generated inside can be effectively discharged in time, and an internal circuit board cannot be damaged.

In order to fix the upper cover plate 1 and the housing 3, at least one screw hole is provided around an edge portion on the other side of the upper cover plate 1, and the screw hole is used for fixing the upper cover plate 1 and the fixed flight control plate 2, and the screw hole is used for fixing the upper cover plate 1 and the housing 3.

Referring to FIGS. 4-5; in order to better complete the fixation of the lower cover plate 5 with the shell 3 and the lower shell 4; the one side of lower apron 5 and casing 3 lock is equipped with the step form boss fixed with lower apron 5, and the step sets up one of them side of boss, and simultaneously, in order to realize guaranteeing to fly the inside stability of accuse shell, casing 3 is equipped with the heating panel on the another side for the heat of inside production can in time effectual discharge, can not damage the internal circuit board.

In order to fix the lower cover 5 and the housing 3, at least one screw hole is provided around an edge portion on the other side of the lower cover 5, and the screw hole is used for one of the lower cover 5 and the lower housing 4 and for the other to fix the lower cover 5 and the housing 3.

Referring to fig. 1, after the hardware structure of the unmanned aerial vehicle controller is simplified to further reduce the volume of the hardware structure, a weight reduction groove is provided in the housing 3 in order to further reduce the mass of the hardware structure.

Referring to FIGS. 1-5; when the flight control system is used, the signal aerial plug wire is inserted into a signal port of the flight control system box and can be interconnected with peripheral electrical equipment. Meanwhile, a direct current power supply of 6-28V is inserted, and the antenna is connected to an antenna interface, so that wireless link data communication is carried out. Fig. 1 is a schematic diagram of the overall structure of the present invention, which shows the positional relationship among the upper cover plate 1, the housing 3 and the lower cover plate 5 as a whole, and clearly shows that the flight control panel 2 completes the internal fixation through the lower bottom shell 4; a peripheral installation area is arranged on the left side of the drawing, a power interface 8 is arranged on the peripheral installation area, and an antenna interface 6 and a signal aerial plug 7 are respectively arranged on two sides of the power interface 8; the access of different peripheral equipment can be realized on the shell 3; fig. 2 is a front view structural schematic diagram of the upper cover plate of the present invention, and fig. 3 is a rear view structural schematic diagram of the upper cover plate of the present invention; in fig. 2 and 3, we can obtain the specific structure of the two sides of the upper cover plate 1, i.e. one side is a rectangular boss, and the other side is a heat dissipation plate and a screw hole; fig. 4 is a rear view structural diagram of the lower cover plate of the present invention, and fig. 5 is a front view structural diagram of the lower cover plate of the present invention; in fig. 4 and 5, we can obtain the specific structure of the two sides of the lower cover plate 5, i.e. one side is a rectangular boss, one side of the rectangular boss is in a step shape, and the other side is a heat dissipation plate and a screw hole; fig. 6 is a schematic diagram of the circuit module connection of the present invention; as shown in fig. 6, a connection mode is given in which the CPU chip is connected to the FPGA chip through the EMIF bus, wherein the power module, the CPU chip, and the FPGA chip; the control source is two paths, wherein one path is accessed to the CPU chip from the ground station, and the other path is transmitted to the receiver through remote control and transmitted to the CPU chip through the receiver; the peripheral equipment is mainly connected with the FPGA chip through PWN pulses; at least one peripheral device is preferably selected from ailerons, throttle, elevator, rudder and other tasks; under the composition of peripheral equipment and control source, unmanned aerial vehicle flight control system can accomplish functions such as voltage acquisition and voltage output.

The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.

Claims

1. The utility model provides an unmanned aerial vehicle flies accuse ware which characterized in that: the flight control device comprises a flight control device shell consisting of an upper cover plate (1), a lower cover plate (5) and a shell (3), wherein a flight control plate (2) is fixed on the lower cover plate (5) through a lower bottom shell (4), and one end of the shell (3) is respectively provided with a power interface (8), a signal aviation plug (7) and an antenna interface (6);

the flight control panel (2) comprises a power supply module, a wireless communication module, a CPU chip and an FPGA chip which are connected through an EMIF bus; the power supply module is connected with the power supply interface (8) and respectively supplies power to the CPU chip and the FPGA chip, and the FPGA chip is connected with the external equipment of the flight controller through the signal aerial plug (7); the wireless communication module is respectively connected with the CPU chip and the antenna interface (6).

2. The unmanned aerial vehicle flight controller of claim 1, wherein: the signal aerial plug (7) comprises RS232, RS422, CAN, PWM, GPIO, ADC and DAC interfaces.

3. A drone flight controller according to claim 1 or 2, characterised in that: the external device of the flight controller sends information to the FPGA chip through the signal aerial plug (7), and the FPGA chip forwards the information to the CPU chip; and a control instruction sent by the CPU chip is sent to the external equipment of the flight controller through the FPGA chip and the signal aerial plug (7).

4. The unmanned aerial vehicle flight controller of claim 1, wherein: the antenna interface (6) is also connected with a wireless antenna, and the CPU chip is in wireless communication with the control source through the wireless communication module and the wireless antenna.

5. An unmanned aerial vehicle flight controller according to claim 1 or 4, wherein: the antenna interface (6) and the signal aerial plug (7) are respectively arranged on two sides of the power interface (8).

6. The unmanned aerial vehicle flight controller of claim 1, wherein: one side of the upper cover plate (1) buckled with the shell (3) is provided with a rectangular boss fixed with the flight control plate (2), and the other side is provided with a heat dissipation plate.

7. The unmanned aerial vehicle flight controller of claim 6, wherein: at least one screw hole is arranged around the upper cover plate (1).

8. The unmanned aerial vehicle flight controller of claim 1, wherein: one side of the lower cover plate (5) buckled with the shell (3) is provided with a step-shaped boss fixed with the lower cover plate (5), and the other side is provided with a heat dissipation plate.

9. The unmanned aerial vehicle flight controller of claim 8, wherein: and at least one screw hole is arranged on the other surface of the lower cover plate.

10. A drone aircraft controller according to claim 1, 6 or 8, characterised in that: and a weight reduction groove is formed in the shell (3).