Mounting structure of double-wire system power supply system

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an installation structure of a double-wire system power supply system. The installation structure of the double-wire system power supply system comprises an unmanned aerial vehicle body, two devices are installed on the unmanned aerial vehicle body through bolts, a cable is connected between the two devices, the outer layer of the cable is wrapped with a cable shielding layer, and connector tail accessories are installed at the ends, connected with the cable shielding layer, of the two devices; the equipment is provided with a power supply positive electrode and a power supply negative electrode, when the power supply negative electrode of the equipment is connected with a shell of the equipment through a grounding wire, an insulating mounting plate is additionally arranged on a bolt for connecting the equipment and the unmanned aerial vehicle body, and a connector tail attachment of the equipment is disconnected from the cable shielding layer. According to the utility model, the double-wire system power supply system is realized by additionally arranging the insulating mounting plate on the bolt for connecting the equipment and the unmanned aerial vehicle body and disconnecting the connector tail attachment of the equipment from the cable shielding layer.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to an installation structure of a two-wire power supply system. Background Art

[0002] At present, the outer shells of medium and large unmanned aerial vehicles mostly adopt the form of skin or composite materials, and the electrical conductivity of the whole machine is not very ideal. If a single-wire power supply is adopted, there will be a large voltage difference between the power supply and the ground, and in the single-wire power supply circuit, the outer shell of the whole machine is equivalent to the negative ground. During testing and flight, any contact between the power supply positive pole and the fuselage shell will cause the short circuit of the equipment, resulting in unimaginable consequences. Therefore, most medium and large unmanned aerial vehicles currently adopt a two-wire power supply circuit.

[0003] Although many unmanned aerial vehicles originally selected a two-wire power supply system in the initial design, many have ignored the situation where the power supply negative pole of the equipment is indirectly connected to the fuselage due to the conduction between the power supply negative pole of the equipment and the equipment shell. In addition, some are due to the connection between the cable shielding layer and the connector tail of the equipment, which also indirectly leads to the change from a two-wire system to a single-wire system.

[0004] The information disclosed in this background art section is only intended to increase the understanding of the overall background of the present 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 present utility model is to overcome the deficiencies in the prior art and provide an installation structure of a two-wire power supply system to solve the technical problem that the equipment installation in the related art indirectly causes the two-wire power supply to become a single-wire power supply.

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

[0007] The present utility model provides an installation structure of a two-wire power supply system, including a drone fuselage. Two devices are installed on the drone fuselage through bolts. A cable is connected between the two devices. The outer layer of the cable is wrapped with a cable shielding layer. Connector tails are installed at one ends of the two devices connecting the cable shielding layer.

[0008] The device has a power supply positive pole and a power supply negative pole. When the power supply negative pole of the device is connected to its shell through a grounding wire, an insulating mounting plate is added to the bolt connecting the device and the drone fuselage, and the connector tail of the device is disconnected from the cable shielding layer.

[0009] Further, the device includes a first device and a second device. The first device is connected to the drone fuselage by a first bolt, and an insulating mounting plate is installed on the first bolt. The second device is connected to the drone fuselage by a second bolt.

[0010] Further, the connector tail attachment of the first device is disconnected from the cable shielding layer, and the connector tail attachment of the second device is connected to the cable shielding layer.

[0011] Further, the negative power supply terminal of the first device is connected to its outer shell through a ground wire, and the negative power supply terminal of the second device is not connected to its outer shell through a ground wire.

[0012] Further, the device includes two first devices. The two first devices are connected to the drone fuselage by first bolts, and insulating mounting plates are installed on both of the first bolts.

[0013] Further, the connector tail attachments of both of the first devices are disconnected from the cable shielding layer.

[0014] Further, the cable shielding layer is connected to the drone fuselage through a shielding layer ground wire.

[0015] Further, the negative power supply terminals of both of the first devices are connected to their outer shells through ground wires.

[0016] Compared with the prior art, the beneficial effects achieved by the present utility model are as follows:

[0017] The present utility model provides an installation structure of a two-wire power supply system. When the negative power supply terminal of a device is connected to its outer shell through a ground wire, a two-wire power supply is realized by adding an insulating mounting plate to the bolt connecting the device and the drone fuselage and disconnecting the connector tail attachment of the device from the cable shielding layer. Description of the Drawings

[0018] Figure 1 is a schematic structural diagram of the installation structure of the two-wire power supply system provided in the first embodiment;

[0019] Figure 2 is a schematic structural diagram of the installation structure of the two-wire power supply system provided in the second embodiment;

[0020] In the figure: 1: drone fuselage; 2: cable; 3: cable shielding layer; 4: connector tail attachment; 5: positive power supply terminal; 6: negative power supply terminal; 7: outer shell; 8: ground wire; 9: insulating mounting plate; 10: first device; 11: second device; 12: first bolt; 13: second bolt; 14: shielding layer ground wire. Detailed Embodiments

[0021] The present utility model will be further described below in conjunction with 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.

[0022] 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.

[0023] In the description of the present utility model, it should be noted that unless otherwise clearly defined and limited, 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. Embodiment

[0024] As Figure 1 shown, this embodiment provides an installation structure of a two-wire power supply system, including a drone fuselage 1, on which a first device 10 and a second device 11 are installed. A cable 2 is connected between the first device 10 and the second device 11. The outer layer of the cable 2 is wrapped with a cable shielding layer 3. One end of the first device 10 and the second device 11 connected to the cable shielding layer 3 are both installed with connector tails 4.

[0025] In this embodiment, the first device 10 is connected to the drone fuselage 1 through a first bolt 12, and the second device 11 is connected to the drone fuselage 1 through a second bolt 13.

[0026] Specifically, both the first device 10 and the second device 11 have a positive power supply terminal 5 and a negative power supply terminal 6. The negative power supply terminal 6 of the first device 10 is connected to its housing 7 through a ground wire 8. In this case, during the installation of the first device 10, the negative power supply terminal 6 of the whole machine will be indirectly conducted to the drone fuselage 1, forming a single-wire system. To avoid this situation, an insulating mounting plate 9 is installed on the first bolt 12.

[0027] The negative power supply terminal 6 of the second device 11 is not connected to its housing 7 through a ground wire 8, that is, the negative power supply terminal 6 of the second device 11 is not conducted to its housing 7. Therefore, the second device 11 can be directly connected to the drone fuselage 1 through the second bolt 13.

[0028] To prevent the cable shielding layer 3 from being conducted to the housing 7 of the second device 11 through the connector tail attachment 4 connecting the second device 11, and thus being conducted to the drone fuselage 1 through the second bolt 13, it is necessary to disconnect the connector tail attachment 4 of the first device 10 from the cable shielding layer 3 here, that is, to insulate the connector tail attachment 4 of the first device 10 from the cable shielding layer 3.

[0029] In this embodiment, by installing an insulating mounting plate 9 on the first bolt 12 of the first device 10 and insulating the connector tail attachment 4 of the first device 10 from the cable shielding layer 3, the dual-wire power supply system of the whole machine is ensured. Through this installation structure, a real dual-wire power supply system is realized, avoiding many short-circuit situations caused by cable wear during testing or flight. Embodiment

[0030] As Figure 2 shown, this embodiment provides an installation structure of a dual-wire power supply system, including a drone fuselage 1. Two first devices 10 are installed on the drone fuselage 1. A cable 2 is connected between the two first devices 10. The outer layer of the cable 2 is wrapped with a cable shielding layer 3. Connector tail attachments 4 are installed at one end of the two first devices 10 connecting the cable shielding layer 3.

[0031] In this embodiment, both of the two first devices 10 are connected to the drone fuselage 1 through first bolts 12. Both of the two first devices 10 have a positive power supply terminal 5 and a negative power supply terminal 6. At the same time, the negative power supply terminals 6 of both of the two first devices 10 are connected to their housings 7 through ground wires 8.

[0032] Specifically, to ensure the dual-wire system of the whole machine power supply system and prevent the negative power supply terminals 6 of the two first devices 10 from being indirectly conducted to the drone fuselage 1, when installing the two first devices 10, insulating mounting plates 9 are installed on both of the two connected first bolts 12.

[0033] In this embodiment, to ensure the shielding effect of the shield layer grounding, a shield layer grounding wire 14 is used to connect the cable shield layer 3 and the UAV fuselage 1.

[0034] Specifically, to prevent the two first devices 10 from being connected to the shield layer grounding wire 14 through the connector tails 4, indirectly causing the negative power supplies 6 of the two first devices 10 to be electrically connected to the UAV fuselage 1, changing from a two-wire system to a single-wire system, the connector tails 4 of the two first devices 10 and the cable shield layer 3 are both insulated here.

Claims

1. An installation structure of a two-wire power supply system, characterized in that, It includes a UAV fuselage (1), on which two devices are installed by bolts. A cable (2) is connected between the two devices. The outer layer of the cable (2) is wrapped with a cable shielding layer (3). At one end where the two devices are connected to the cable shielding layer (3), a connector tail attachment (4) is installed on each; The device has a power supply positive electrode (5) and a power supply negative electrode (6). When the power supply negative electrode (6) of the device is connected to its outer shell (7) through a ground wire (8), an insulating mounting plate (9) is additionally provided on the bolt connecting the device and the UAV fuselage (1), and the connector tail attachment (4) of the device is disconnected from the cable shielding layer (3).

2. The installation structure of the two-wire power supply system according to claim 1, characterized in that, The device includes a first device (10) and a second device (11). The first device (10) is connected to the UAV fuselage (1) through a first bolt (12), and an insulating mounting plate (9) is installed on the first bolt (12). The second device (11) is connected to the UAV fuselage (1) through a second bolt (13).

3. The installation structure of the two-wire power supply system according to claim 2, characterized in that, The connector tail attachment (4) of the first device (10) is disconnected from the cable shielding layer (3), and the connector tail attachment (4) of the second device (11) is connected to the cable shielding layer (3).

4. The installation structure of the two-wire power supply system according to claim 3, characterized in that, The power supply negative electrode (6) of the first device (10) is connected to its outer shell (7) through a ground wire (8), and the power supply negative electrode (6) of the second device (11) is not connected to its outer shell (7) through a ground wire (8).

5. The installation structure of the two-wire power supply system according to claim 1, characterized in that The device includes two first devices (10). The two first devices (10) are connected to the UAV fuselage (1) through first bolts (12), and insulating mounting plates (9) are installed on both of the first bolts (12).

6. The installation structure of the two-wire power supply system according to claim 5, characterized in that The connector tail attachments (4) of the two first devices (10) are both disconnected from the cable shielding layer (3).

7. The installation structure of the two-wire power supply system according to claim 6, characterized in that, The cable shielding layer (3) is connected to the UAV fuselage (1) through a shielding layer ground wire (14).

8. The installation structure of the two-wire power supply system according to claim 7, characterized in that, The power supply negative electrodes (6) of the two first devices (10) are both connected to their outer shells (7) through ground wires (8).

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