Unmanned aerial vehicle avionics system and unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle avionics system and an unmanned aerial vehicle. The unmanned aerial vehicle avionics system comprises an FCU shell and a PMU shell, an FCU circuit board and an image transmission module circuit board are installed in the FCU shell, a PMU circuit board is installed in the PMU shell, the FCU circuit board and the image transmission module circuit board are arranged in a laminated mode, and a power supply terminal used for being connected with the PMU shell is installed on the FCU shell. The FCU and the PMU are independently and separately designed through the FCU shell and the PMU shell, coupling of the FCU and the PMU is reduced, and therefore the flight safety of the unmanned aerial vehicle is improved; and meanwhile, the FCU circuit board and the image transmission module circuit board are arranged in the FCU shell in an up-and-down laminated manner, so that the space in the FCU shell is effectively utilized, and the FCU shell is more compact as much as possible.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to an avionics system and an unmanned aerial vehicle for an unmanned aerial vehicle. Background Art

[0002] Due to its small size and flexible operation, unmanned aerial vehicles are widely used in operation scenarios such as sowing, surveying and mapping, spraying, and hoisting, so as to meet the operation requirements of crop fertilization, pest control, cargo transportation, etc.

[0003] The control brain of the above task system depends on the flight control system of the unmanned aerial vehicle. At present, the flight control technical solution of the unmanned aerial vehicle mainly integrates the FCU (flight control unit) and the PMU (power management unit) in an avionics housing. Inevitably, if the PMU fails, the FCU cannot be used continuously, which will affect the flight safety of the unmanned aerial vehicle.

[0004] The information disclosed in this background art section is only intended to increase the understanding of the overall background of the utility model, and should not be regarded as an admission or any form of suggestion that this information constitutes the prior art already known to those of ordinary skill in the art. Summary of the Utility Model

[0005] The purpose of the utility model is to overcome the deficiencies in the prior art and provide an avionics system and an unmanned aerial vehicle for an unmanned aerial vehicle, so as to solve the problem that the integration of the FCU and the PMU in an avionics housing in the related art is likely to affect the flight safety of the unmanned aerial vehicle.

[0006] To solve the above technical problems, the utility model is implemented by adopting the following technical solutions:

[0007] On the one hand, the utility model provides an avionics system for an unmanned aerial vehicle, which includes an FCU housing and a PMU housing. An FCU circuit board and a video transmission module circuit board are installed inside the FCU housing, a PMU circuit board is installed inside the PMU housing, the FCU circuit board and the video transmission module circuit board are arranged in a stacked manner, and a power supply terminal for connecting with the PMU housing is installed on the FCU housing.

[0008] Further, the FCU housing and the PMU housing are fixed to the fuselage frame by bolts, and heat-conducting paste is provided on the contact surface between the FCU housing and the PMU housing and the fuselage frame.

[0009] Further, the FCU housing includes an FCU upper shell and an FCU lower shell, and an accommodation cavity for installing the FCU circuit board and the video transmission module circuit board is formed between the FCU upper shell and the FCU lower shell;

[0010] The PMU housing includes a PMU upper shell and a PMU lower shell, and a receiving cavity for installing the PMU circuit board is formed between the PMU upper shell and the PMU lower shell.

[0011] Further, a sealing ring is installed between the FCU upper shell and the FCU lower shell.

[0012] Further, a plurality of signal terminals and heat dissipation teeth are installed on both the FCU upper shell and the PMU upper shell.

[0013] Further, a plurality of antenna terminals are also installed on the FCU upper shell.

[0014] Further, a barometer is installed inside the FCU lower shell.

[0015] Further, a battery is installed on the PMU circuit board, and a battery installation cavity for accommodating the battery is formed on the PMU upper shell.

[0016] Further, a battery cover for covering the battery installation cavity is installed on the PMU upper shell.

[0017] On the other hand, the present utility model provides an unmanned aerial vehicle, including the above-mentioned avionics system of the unmanned aerial vehicle.

[0018] Compared with the prior art, the beneficial effects achieved by the present utility model are as follows:

[0019] By independently separating and designing the FCU and the PMU through the FCU housing and the PMU housing, the present utility model reduces the coupling between the FCU and the PMU, thereby improving the flight safety of the unmanned aerial vehicle; at the same time, the FCU circuit board and the video transmission module circuit board are stacked up and down inside the FCU housing to effectively utilize the space inside the FCU housing and make the FCU housing as compact as possible. Description of the Drawings

[0020] Figure 1 is a schematic structural diagram of an unmanned aerial vehicle provided by an embodiment of the present utility model;

[0021] Figure 2 is a schematic structural diagram of an avionics system of an unmanned aerial vehicle provided by an embodiment of the present utility model;

[0022] Figure 3 is an exploded view of an FCU housing provided by an embodiment of the present utility model;

[0023] Figure 4 is an exploded view of a PMU housing provided by an embodiment of the present utility model;

[0024] In the figure: 1: FCU housing; 2: PMU housing; 3: FCU circuit board; 4: video transmission module circuit board; 5: PMU circuit board; 6: power supply terminal; 7: fuselage frame; 8: FCU upper shell; 9: FCU lower shell; 10: PMU upper shell; 11: PMU lower shell; 12: sealing ring; 13: signal terminal; 14: heat dissipation teeth; 15: antenna terminal; 16: barometer; 17: battery; 18: battery installation cavity; 19: battery cover. Detailed implementation mode

[0025] The present utility model will be further described below with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present utility model, and cannot be used to limit the protection scope of the present utility model.

[0026] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present utility model, unless otherwise specified, the meaning of "a plurality" is two or more. Embodiment 1:

[0027] As Figures 1-4 shown, this embodiment provides an avionics system for an unmanned aerial vehicle, including an FCU housing 1 and a PMU housing 2, and the FCU housing 1 and the PMU housing 2 are fixed to the fuselage frame 7 by bolts.

[0028] Specifically, the FCU housing 1 and the PMU housing 2 can be made of metal, plastic, or other materials.

[0029] In this embodiment, a heat-conducting paste is provided on the contact surface between the FCU housing 1 and the PMU housing 2 and the fuselage frame 7 for effective heat dissipation.

[0030] In this embodiment, the FCU housing 1 includes an FCU upper housing 8 and an FCU lower housing 9. The FCU lower housing 9 is assembled with the FCU upper housing 8 by bolts, and a receiving cavity for installing the FCU circuit board 3 and the video transmission module circuit board 4 is formed between the FCU upper housing 8 and the FCU lower housing 9.

[0031] Specifically, the FCU circuit board 3 and the video transmission module circuit board 4 are stacked vertically inside the FCU housing 1 to effectively utilize the space inside the FCU housing and make the FCU housing as compact as possible.

[0032] In this embodiment, a sealing ring 12 is installed between the FCU upper housing 8 and the FCU lower housing 9. The sealing ring 12 is used to seal the electronic components inside the FCU housing and prevent dust or liquid from entering the inside of the FCU housing 1, thereby improving the service life and stability of the UAV avionics system.

[0033] In this embodiment, a plurality of signal terminals 13, heat dissipation teeth 14 and antenna terminals 15 are installed on the FCU upper housing 8, and a barometer 16 is installed inside the FCU lower housing 9.

[0034] Specifically, the signal terminals are used to transmit the signals of the power motor, radar and camera of the UAV to the FCU, and then control the power system and perception system of the UAV; the heat dissipation teeth 14 are used for effective heat dissipation; the antenna terminals are used to transmit wireless signals to confirm the position of the UAV; the barometer is used for UAV navigation and accurately estimating its ascending and descending speeds.

[0035] In this embodiment, the PMU housing 2 includes a PMU upper housing 10 and a PMU lower housing 11. The PMU lower housing 11 is assembled with the PMU upper housing 10 by bolts, and a receiving cavity for installing the PMU circuit board 5 is formed between the PMU upper housing 10 and the PMU lower housing 11.

[0036] Specifically, a battery 17 is installed on the PMU circuit board 5. A battery installation cavity 18 for accommodating the battery 17 is provided on the PMU upper housing 10, and a battery cover 19 for covering the battery installation cavity 18 is installed on the PMU upper housing 10.

[0037] In this embodiment, a power supply terminal 6 for connecting with the PMU housing 2 is installed on the FCU housing 1, and the PMU supplies power to the FCU through the power supply terminal 6.

[0038] In this embodiment, the FCU and the PMU are independently designed separately by the FCU housing 1 and the PMU housing 2, thereby reducing the coupling between the FCU and the PMU. Even when the PMU fails, it can be separately disassembled for repair without affecting the FCU, thus improving the flight safety of the drone. Embodiment 2:

[0039] This embodiment provides a drone, including the avionics system of the drone described in Embodiment 1.

[0040] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood through specific situations.

Claims

1. An avionics system for an unmanned aerial vehicle, characterized in that: The invention comprises an FCU housing (1) and a PMU housing (2), wherein an FCU circuit board (3) and an image transmission module circuit board (4) are installed inside the FCU housing (1), and a PMU circuit board (5) is installed inside the PMU housing (2), wherein the FCU circuit board (3) and the image transmission module circuit board (4) are stacked, and a power supply terminal (6) for connecting to the PMU housing (2) is installed on the FCU housing (1).

2. The UAV avionics system according to claim 1, characterized in that: The FCU housing (1) and the PMU housing (2) are fixed to a fuselage frame (7) by means of bolts, and thermal conductive paste is provided on contact surfaces between the FCU housing (1) and the PMU housing (2) and the fuselage frame (7).

3. The UAV avionics system according to claim 1, characterized in that: The FCU housing (1) comprises an FCU upper shell (8) and an FCU lower shell (9), wherein a receiving cavity for mounting the FCU circuit board (3) and the image transmission module circuit board (4) is formed between the FCU upper shell (8) and the FCU lower shell (9); The PMU housing (2) comprises a PMU upper shell (10) and a PMU lower shell (11), and a receiving cavity for mounting the PMU circuit board (5) is formed between the PMU upper shell (10) and the PMU lower shell (11).

4. The UAV avionics system according to claim 3, characterized in that: A sealing ring (12) is installed between the FCU upper shell (8) and the FCU lower shell (9).

5. The UAV avionics system according to claim 3, characterized in that: A plurality of signal terminals (13) and heat dissipation teeth (14) are installed on both the FCU upper shell (8) and the PMU upper shell (10).

6. The UAV avionics system according to claim 3, characterized in that: A plurality of antenna terminals (15) are also mounted on the FCU upper shell (8).

7. The UAV avionics system according to claim 3, characterized in that: A barometer (16) is installed in the FCU lower shell (9).

8. The UAV avionics system according to claim 3, characterized in that: A battery (17) is installed on the PMU circuit board (5), and a battery installation cavity (18) for accommodating the battery (17) is provided on the PMU upper shell (10).

9. The UAV avionics system according to claim 8, characterized in that: A battery cover (19) for covering the battery installation cavity (18) is installed on the PMU upper shell (10).

10. A drone, characterized in that: A UAV avionics system comprising any one of claims 1-9.

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