CN218415356U - Aircraft distribution box - Google Patents

Abstract

The utility model belongs to the technical field of electric aircraft power distribution, and relates to an aircraft power distribution box. The aircraft power distribution box includes a box body and a positive copper bar module installed on the box body, a negative copper bar module, a plurality of power supply input ports and a plurality of output ports, and the positive copper bar module is electrically connected to the Between the positive terminals of the multiple power input ports, the negative copper bar module is electrically connected between the negative poles of the multiple power input ports, and the positive pole of each output port is connected to the positive terminal through a safety module. The positive electrode copper bar module is electrically connected, and the negative electrode of each output port is electrically connected to the negative electrode copper bar module. The aircraft power distribution box, when one of the power input ports of the aircraft fails, can continue to supply power to various parts of the aircraft through other power input ports, preventing power interruptions from causing the aircraft to fall, and at the same time improving the power supply safety performance of the aircraft.

Description

Aircraft distribution box

technical field

The utility model belongs to the technical field of electric aircraft power distribution, in particular to an aircraft power distribution box.

Background technique

In the prior art, the power distribution scheme of the electric aircraft is concentrated on the system level, and the power distribution design of the PDU (Protocol Data Unit) structure is rarely disclosed. Referring to the power distribution design of other electric devices, there is a power distribution box in the field of electric vehicles, but it only has one power source, which is internally distributed to DC-DC, motor, PTC, etc. for power supply. If it is directly used in an electric aircraft, once the power supply fails, the power will be interrupted and cause the aircraft to fail and fall, thereby causing damage to the aircraft.

Utility model content

The technical problem to be solved by the utility model is: aiming at the technical problem that the power will be interrupted once the power supply of the existing shock absorber fails, an aircraft power distribution box is provided.

In order to solve the above technical problems, the embodiment of the utility model provides an aircraft power distribution box, including a box body and a positive copper bar module, a negative copper bar module, a plurality of power input ports and a plurality of output ports, the positive copper bar module is electrically connected between the positive terminals of the multiple power input ports, and the negative copper bar module is electrically connected between the negative terminals of the multiple power input ports, The positive pole of each output port is electrically connected to the positive copper busbar module through a safety module, and the negative pole of each output port is electrically connected to the negative copper busbar module.

The aircraft power distribution box according to the embodiment of the utility model is improved based on the vehicle-mounted power distribution box, and based on the safety redundancy design requirements of the aircraft, multiple power input ports are used for power distribution settings, and a positive copper bar is installed inside the box body Module and negative copper bar module, so that the positive and negative poles of each output port are electrically connected with the positive copper bar module and the negative electrode copper bar module, so that multiple power input ports can be connected to each output port at the same time or separately The function of electrically connected parts to provide power. When one of the power input ports of the aircraft fails, the other power input ports can be used to continuously supply power to various parts of the aircraft, preventing power interruptions from causing the aircraft to fall, and at the same time improving the power supply safety performance of the aircraft.

Optionally, the plurality of power input ports include a first input port and a second input port;

The positive copper bar module includes a first copper bar, a second copper bar and a third copper bar connected between the first copper bar and the second copper bar, the first copper bar and the The positive terminal of the first input port is electrically connected, and the second copper bar is electrically connected to the positive terminal of the second input port;

Among the plurality of output ports, the positive poles of some of the output ports are electrically connected to the first copper bar through the corresponding insurance module, and the positive poles of the other output ports are connected to the first copper bar through the corresponding insurance module. Two copper bars are connected.

Optionally, the insurance module includes a fuse.

Optionally, the negative copper bar module includes a fourth copper bar, and the fourth copper bar is electrically connected between the negative pole of the first input port and the negative pole of the second input port;

The negative electrode of each output port is electrically connected to the fourth copper bar.

Optionally, the multiple output ports include one DC-DC output port and multiple MCU output ports.

Optionally, there are six MCU output ports.

Optionally, the positive electrodes of each output port are electrically connected to the corresponding insurance module through a first high-voltage wire harness;

The negative electrode of each output port is electrically connected to the fourth copper bar through a second high-voltage wire harness.

Optionally, each of the first high-voltage wire harnesses and each of the second high-voltage wire harnesses can be installed in the box through a wire harness buckle.

Optionally, the aircraft power distribution box also includes several electrical connection components;

Between the first high-voltage wire harness and the corresponding insurance module, between the first copper bar and the corresponding insurance module, between the second copper bar and the corresponding insurance module, and between the The second high-voltage wire harness is electrically connected to the corresponding fourth copper bar through the electrical connection assembly.

Optionally, the electrical connection assembly includes a mounting bracket and a mounting bolt, one end of the mounting bracket is installed on the box, and an inner screw hole is formed on the mounting bracket, and the mounting bolt can be connected to the inner Screw thread connection.

Description of drawings

Fig. 1 is a schematic structural view of an aircraft power distribution box provided by an embodiment of the utility model;

Fig. 2 is a schematic diagram of the internal structure of the aircraft power distribution box provided by an embodiment of the utility model;

Fig. 3 is a schematic structural view of the mounting bracket in Fig. 2;

FIG. 4 is a schematic structural diagram of the positive copper bar module and the negative copper bar module in FIG. 2 .

The reference signs in the instructions are as follows:

1. Box body; 11. Box connection structure;

2. Positive copper bar module; 21. The first copper bar; 22. The second copper bar; 23. The third copper bar;

3. Negative electrode copper bar module; 31. The fourth copper bar;

4. Power input port; 41. First input port; 42. Second input port;

5. Output port; 51. DC-DC output port; 52. MCU output port;

6. Insurance module;

7. The first high-voltage wiring harness;

8. The second high-voltage wiring harness;

9. Electrical connection components; 91. Mounting bracket; 911. Internal screw holes.

Detailed ways

In order to make the technical problems, technical solutions and beneficial effects solved by the utility model clearer, the utility model will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model, and are not intended to limit the utility model.

As shown in Figures 1 to 4, the aircraft power distribution box provided by the embodiment of the utility model includes a box body 1 and a positive copper bar module 2 installed on the box body 1, a negative copper bar module 3, multiple A power input port 4 and a plurality of output ports 5, the positive copper bar module 2 is electrically connected between the positive poles of the plurality of power input ports 4, and the negative copper bar module 3 is electrically connected to a plurality of the positive electrodes of the power input ports 4. Between the negative poles of the power input ports 4, the positive poles of each of the output ports 5 are electrically connected to the positive copper bar module 2 through a safety module 6, and the negative poles of each of the output ports 5 are connected to the The negative electrode copper bar module 3 is electrically connected.

The aircraft power distribution box provided by the embodiment of the utility model is improved based on the vehicle-mounted power distribution box, and based on the safety redundancy design requirements of the aircraft, a plurality of power supply input ports 4 are used for power distribution settings, and a positive pole is set inside the box body 1 The copper bar module 2 and the negative electrode copper bar module 3 make the positive and negative poles of each output port 5 electrically connected to the positive electrode copper bar module 2 and the negative electrode copper bar module 3 respectively, realizing that multiple power input ports 4 can The function of simultaneously or individually supplying power to components electrically connected to each output port 5 . When one of the power input ports 4 of the aircraft fails, the other power input ports 4 can also continuously supply power to various components of the aircraft, preventing power interruptions from causing the aircraft to fall, and at the same time improving the power supply safety performance of the aircraft.

In one embodiment, as shown in FIG. 1 and FIG. 2 , the power input port 4 is in the shape of a double-circle semi-ring, and includes two terminals connected to the external positive and negative electrodes respectively. In the embodiment of the present invention, the terminal connected to the external positive pole of the power input port 4 is named as the positive terminal of the power input port 4, and the terminal connected to the external negative pole of the power input port 4 is named as Negative terminal of the above-mentioned power input port 4.

In one embodiment, as shown in FIG. 1 , FIG. 2 and FIG. 4 , the plurality of power input ports 4 include a first input port 41 and a second input port 42 .

The positive copper bar module 2 includes a first copper bar 21, a second copper bar 22, and a third copper bar 23 connected between the first copper bar 21 and the second copper bar 22. A copper bar 21 is electrically connected to the positive terminal of the first input port 41 , and the second copper bar 22 is electrically connected to the positive terminal of the second input port 42 .

Among the plurality of output ports 5, the positive poles of some of the output ports 5 are electrically connected to the first copper bar 21 through the corresponding insurance module 6, and the positive poles of other output ports 5 are electrically connected through the corresponding insurance modules 6. Group 6 is electrically connected to the second copper bar 22 .

By electrically connecting the first copper bar 21 and the second copper bar 22 to the positive terminals of two input ports (the first input port 41 and the second input port 42 ), and connecting the The third copper bar 23 is electrically connected between the first copper bar 21 and the second copper bar 22, thereby enabling equipotential connection and power distribution between the three positive copper bars to prevent failure of one of the input ports of the aircraft resulting in a power interruption.

In one embodiment, as shown in FIG. 1 , FIG. 2 and FIG. 4 , the negative electrode copper bar module 3 includes a fourth copper bar 31 , and the fourth copper bar 31 is electrically connected to the first input port 41 between the negative pole of the second input port 42 and the negative pole of the second input port 42 .

The negative electrode of each output port 5 is electrically connected to the fourth copper bar 31 .

The fourth copper bar 31 is used to connect the negative sides of the two input ports, so as to perform equipotential connection internally. Its function is to prevent power interruption caused by failure of one of the input ports of the aircraft. It is possible to integrate the output positive and negative terminals to simplify the internal high voltage circuit.

In one embodiment, as shown in FIG. 1 and FIG. 2 , the multiple output ports 5 include a DC-DC output port 51 and multiple MCU output ports 52 .

In the illustrated embodiment, the output ports 5 are provided with seven, wherein, the MCU output ports 52 are provided with six, and the six MCU output ports 52 are respectively marked as: 52a, 52b, 52c, 52d, 52e, 52f. In each of the MCU output ports 52, the DC-DC output port 51 is electrically connected to three of the MCU output ports 52 and the first copper bar 21, and the other three MCU output ports 52 are electrically connected to the first copper bar 21. The second copper bar 22 is electrically connected.

The anode of each MCU output port 52 corresponds to an insurance module 6, and the anode of the DC-DC output port 51 is also correspondingly provided with an insurance module 6 for DC-DC output port 51 and MCU output respectively. Overcurrent protection for port 52.

In one embodiment, as shown in FIG. 1 and FIG. 2 , the number of the insurance modules 6 is consistent with the number of the output ports 5 and is set in one-to-one correspondence. The insurance module 6 includes a circular fuse, one end of the fuse is electrically connected to the output port 5, and the other end is electrically connected to the corresponding copper bar.

In one embodiment, as shown in FIG. 1 and FIG. 2 , the anodes of the output ports 5 are respectively electrically connected to the corresponding insurance modules 6 through a first high-voltage harness 7 . The negative electrode of each output port 5 is electrically connected to the fourth copper bar 31 through a second high voltage harness 8 .

Connect each of the output ports 5 and the corresponding insurance module 6 through a high-voltage wire harness to realize the connection between the insurance and the output port 5. At the same time, using its flexible installation convenience, it can be better installed in the box body 1 of the distribution box. Arrange the wiring harness to save space.

In one embodiment, in order to further simplify the wiring arrangement in the box body 1 and save the space in the box body 1, two screws can be used to fix the four second high-voltage wire harnesses 8 in the middle of the fourth copper bar 31 .

In one embodiment, as shown in FIG. 1 to FIG. 4 , each of the first high-voltage wire harnesses 7 and each of the second high-voltage wire harnesses 8 can be installed in the box body 1 through a wire harness buckle, So that the utilization space inside the box can be further improved.

In one embodiment, as shown in FIGS. 1 and 2 , the aircraft power distribution box further includes several electrical connection components 9 . Between the first high-voltage wire harness 7 and the corresponding insurance module 6, between the first copper bar 21 and the corresponding insurance module 6, between the second copper bar 22 and the corresponding insurance module 6 and/or between the second high-voltage wire harness 8 and the corresponding fourth copper bar 31 are electrically connected through the electrical connection assembly 9 .

In one embodiment, as shown in FIG. 1 and FIG. 2 , the electrical connection assembly 9 includes a mounting bracket 91 and mounting bolts, one end of the mounting bracket 91 is installed on the box body 1, and the mounting bracket 91 An inner screw hole 911 is formed on the top, and the mounting bolt can be threadedly connected with the inner screw hole 911 to lock the component.

Preferably, the mounting bracket 91 is in a cylindrical shape, one end of the mounting bracket 91 is welded and fixed with the box body 1 , and the other end can be connected with a mounting bolt for fixing parts such as insurance. Specifically, the ends of copper bars, high-voltage wire harnesses and/or fuses can be arranged corresponding to the inner screw holes 911 of the installation bracket 91, and then the installation bolts can be screwed into the inner screw holes 911 to lock the copper row, high voltage wiring harness and/or fuse. In addition, the copper bars, high-voltage wire harnesses and/or fuses are connected through the electrical connection assembly 9, so that the space utilization rate in the box body 1 can be better utilized.

In one embodiment, as shown in FIG. 1, several box connection structures 11 are provided on the edge of the box body 1, and the box body connection structures 11 are used to install the box body 1 of the distribution box on the fly. On the main body of the injector, the installation of the distribution box is realized.

The above descriptions are only preferred embodiments of the present utility model, and are not intended to limit the present utility model. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present utility model shall be included in this utility model. within the scope of protection of utility models.

Claims (10)

1. The utility model provides an aircraft block terminal, its characterized in that includes the box and installs anodal copper bar module, negative pole copper bar module, a plurality of power input port and a plurality of output port on the box, anodal copper bar module electricity is connected a plurality of between power input port's the positive terminal, negative pole copper bar module electricity is connected a plurality of between power input port's the negative pole, each the anodal of output port all through an insurance module with anodal copper bar module electricity is connected, each the negative pole of output port all with negative pole copper bar module electricity is connected.

2. The aircraft electrical distribution box of claim 1, wherein the plurality of power input ports comprises a first input port and a second input port;

the positive copper bar module comprises a first copper bar, a second copper bar and a third copper bar connected between the first copper bar and the second copper bar, the first copper bar is electrically connected with the positive terminal of the first input port, and the second copper bar is electrically connected with the positive terminal of the second input port;

in the output ports, the anodes of part of the output ports are electrically connected with the first copper bar through the corresponding safety modules, and the anodes of other output ports are electrically connected with the second copper bar through the corresponding safety modules.

3. The aircraft electrical distribution box of claim 2, wherein the fuse module comprises a fuse.

4. The aircraft power distribution box of claim 2, wherein the negative copper bar module comprises a fourth copper bar electrically connected between the negative electrode of the first input port and the negative electrode of the second input port;

and the cathode of each output port is electrically connected with the fourth copper bar.

5. The aircraft power distribution box of claim 4, wherein the plurality of output ports comprises a DC-DC output port and a plurality of MCU output ports.

6. The aircraft power distribution box of claim 5 wherein said MCU output ports are provided in the number of six.

7. The aircraft distribution box of claim 4, wherein the positive electrode of each output port is electrically connected to the corresponding safety module by a first high voltage wire harness;

and the negative electrode of each output port is electrically connected with the fourth copper bar through a second high-voltage wire harness.

8. The aircraft electrical distribution box of claim 7, wherein each of said first high voltage wire harnesses and each of said second high voltage wire harnesses are mountable within said box by a harness snap fit.

9. The aircraft electrical distribution box of claim 7, further comprising a plurality of electrical connection assemblies;

the first high-voltage wire harness is electrically connected with the corresponding fuse modules, the first copper bar is electrically connected with the corresponding fuse modules, the second copper bar is electrically connected with the corresponding fuse modules, and the second high-voltage wire harness is electrically connected with the corresponding fourth copper bar through the electric connection assembly.

10. The aircraft power distribution box of claim 9, wherein the electrical connection assembly comprises a mounting bracket and a mounting bolt, wherein one end of the mounting bracket is mounted on the box body, the mounting bracket is formed with an internal threaded hole, and the mounting bolt is threadably connected to the internal threaded hole.

Images