Electrical integration system for aircraft battery system

Abstract

The present application relates to the technical field of batteries. Disclosed are an electrical integration system for an aircraft battery system. The electrical integration system comprises: an upper housing outer cover, a lower housing outer cover and a bottom plate, wherein the upper housing outer cover and the lower housing outer cover define a first integrated space, and the lower housing outer cover and the bottom plate define a second integrated space. The first integrated space comprises: a current sensing module, which is used for sensing the current magnitude and direction of each battery pack; a plurality of contactor modules, which are used for controlling the on-off of a high-voltage loop of each electrical integration system; and a pre-charging module, which is used for preventing each contactor module from arcing. The second integrated space comprises: a power source module, which is used for supplying power to each module of the electrical integration system; a control module, which is used for collecting operation information of each battery pack; and a wire harness, which is used for electrically connecting each of the power source module and the control module to the current sensing module, the contactor module and the pre-charging module. Individual modules are combined and integrated into one module, such that external wire harnesses are reduced, thereby reducing the installation difficulty.

Description

Electrical integration systems for aircraft battery systems Technical Field

[0001] The present application relates to the field of battery technology, and in particular to an electrical integration system for an aircraft battery system. Background Art

[0002] The current aircraft battery control system consists of multiple modules, such as the PEU (power electronic control unit) module, positive and negative terminal junction box, charging box, etc. These modules take up a lot of space, are interconnected, have a large number of messy wiring harnesses, are bulky and overweight, posing great challenges to installation and subsequent maintenance.

[0003] Summary of the Invention

[0004] The purpose of the present application is to provide an electrical integration system for an aircraft battery system. The utility model reduces external wiring harnesses, reduces installation difficulty, and reduces system weight by integrating individual modules into one module.

[0005] In order to solve the above technical problems, the present application provides an electrical integration system for an aircraft battery system, wherein the battery system includes multiple battery packs, including: an upper shell cover, a lower shell cover and a bottom plate, the upper shell cover and the lower shell cover are connected together to form a first integrated space, and the lower shell cover and the bottom plate are connected together to form a second integrated space; the first integrated space includes: a current sensing module for sensing the current magnitude and direction of each battery pack; multiple contactor modules for controlling the on and off of the high-voltage circuit of each electrical integration system; a pre-charging module for preventing the contactor module from arcing; the second integrated space includes: a power module for supplying power to each module of the electrical integration system; a control module for collecting working information of each battery pack; a wiring harness for electrically connecting the power module and the control module to the current sensing module, the contactor module and the pre-charging module respectively, so as to send power signals and control signals to the current sensing module, the contactor module and the pre-charging module.

[0006] Optionally, the first integrated space further includes a fuse module, which is used to protect the electrical integrated system from internal short circuit.

[0007] Optionally, the current sensing module, the multiple contactor modules, the pre-charge module and the fuse module are all bolted to the surface of the lower shell cover.

[0008] Optionally, an electrical connector is further included, and the multiple contactor modules are connected in parallel with the fuse module via the electrical connector.

[0009] Optionally, the side surface of the lower shell cover includes a plurality of openings, and the wiring harness portion passes through the openings and is respectively connected to the current sensing module, the contactor module, the pre-charge module and the insurance module.

[0010] Optionally, the bottom edge of the lower shell cover further includes a fixing portion, and the fixing portion is used to be connected to the aircraft.

[0011] Optionally, the operating information includes at least the voltage and temperature of the battery cells in the battery pack.

[0012] The utility model combines multiple modules into one module for assembly, thereby reducing the types and quantity of external wiring harnesses, lowering the difficulty of installation, and reducing the weight of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] FIG1 is a schematic structural diagram of an electrical integration system for an aircraft battery system according to an embodiment of the present application;

[0014] FIG2 is a schematic structural diagram of an electrical integration system without an upper shell cover according to an embodiment of the present application. DETAILED DESCRIPTION

[0015] The following embodiments further illustrate the technical solutions of the present application. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application. It should also be noted that, for ease of description, only portions relevant to the present application are shown in the accompanying drawings, not all of them.

[0016] In the description of this application, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed or detachable connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application in specific contexts.

[0017] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0018] The following describes an embodiment of the present application with reference to the accompanying drawings. As shown in Figures 1 and 2, the embodiment of the present application provides an electrical integration system for an aircraft battery system, wherein the battery system includes multiple battery packs, and the electrical integration system includes: an upper shell cover 1, a lower shell cover 2 and a base plate 3, wherein the upper shell cover 1 and the lower shell cover 2 are connected together to form a first integrated space, and the lower shell cover 2 and the base plate 3 are connected together to form a second integrated space; the first integrated space includes a current sensing module 11, multiple contactor modules 12 and a pre-charge module 13, wherein the current sensing module 11 is used to sense the current size and direction of each battery pack; the multiple contactor modules 12 are used to control the high-voltage circuit of each electrical integration system; the pre-charge module 13 is used to prevent the contactor module 12 from arcing, and the pre-charge module 13 includes a pre-charge contactor 131 and a pre-charge resistor 132. The second integrated space includes a power module 21, a control module 22, and a wiring harness 23. The power module 21 is used to supply power to each module of the electrical integration system, and the control module 22 is used to collect the operating information of each battery pack, as well as provide charge and discharge control, low-voltage control, protection, and monitoring of the operation of the high-voltage system for the high-voltage system. The operating information includes at least the voltage and temperature information of the battery cells in the battery pack. The wiring harness 23 is used to electrically connect the power module and the control module 22 to the current sensing module 11, the contactor module 12, and the pre-charge module 13, respectively, to send power signals and control signals to the current sensing module 11, the contactor module 12, and the pre-charge module 13. By assembling each module into one module, the present utility model reduces the types and number of external wiring harnesses, reduces the difficulty of installation, and reduces the weight of the system.

[0019] Furthermore, the first integrated space also includes a fuse module 14, which is used to protect the electrical integrated system to provide circuit overload and short-circuit protection. The current sensing module 11, multiple contactor modules 12, pre-charge module 13 and fuse module 14 are all bolted to the upper surface of the lower shell cover 2. The first integrated space also includes an electrical connector 15, and multiple contactor modules 12 are connected in parallel with the fuse module 14 through the electrical connector 15. The side of the lower shell cover 2 includes multiple openings, and the wiring harness part passes through the openings and is connected to the current sensing module 11, contactor module 12, pre-charge module 13 and fuse module 14 respectively, that is, it is installed with each module through their respective connectors. The bottom edge of the lower shell cover 2 also includes a fixing portion 20, which is used to connect to the aircraft. The embodiment of the present application integrates various modules into the first integrated space and the second integrated space. The integrated electrical integrated system can provide charging and discharging control, circuit overload and short-circuit protection, voltage sampling, low-voltage control and other functions for the high-voltage system, protecting and monitoring the operation of the high-voltage system. At the same time, after system integration, the number of flying wires is reduced, the number of modules is reduced, the overall weight is reduced, and the weight distribution of the whole machine is more reasonable.

[0020] The above embodiments are merely illustrative of the principles and effects of this application. Anyone skilled in the art may modify or alter the above embodiments without departing from the objectives of this application. Therefore, all equivalent modifications or alterations made by persons skilled in the art without departing from the objectives disclosed herein are intended to be covered by the claims of this application.

Claims

1. An electrical integration system for an aircraft battery system, the battery system comprising a plurality of battery packs, characterized in that: include: An upper shell cover (1), a lower shell cover (2) and a bottom plate (3), wherein the upper shell cover (1) and the lower shell cover (2) are connected together to form a first integrated space, and the lower shell cover (2) and the bottom plate (3) are connected together to form a second integrated space; The first integrated space includes: A current sensing module (11), used for sensing the current magnitude and direction of each battery pack; A plurality of contactor modules (12) for controlling the on and off of high-voltage circuits of each of the electrical integrated systems; A pre-charging module (13) for preventing the contactor module (12) from arcing; The second integrated space includes: A power module (21), used to supply power to each module of the electrical integration system; A control module (22), used for collecting operating information of each of the battery packs; A wiring harness (23) is used to electrically connect the power module and the control module (22) to the current sensing module (11), the contactor module (12) and the pre-charging module (13) respectively, so as to send a power signal and a control signal to the current sensing module (11), the contactor module (12) and the pre-charging module (13).

2. The electrical integration system for an aircraft battery system according to claim 1, characterized in that: The first integrated space also includes a fuse module (14), and the fuse module (14) is used to protect the electrical integrated system from internal short circuit.

3. The electrical integration system for an aircraft battery system according to claim 2, characterized in that: The current sensing module (11), the plurality of contactor modules (12), the pre-charging module (13) and the fuse module (14) are all bolted to the surface of the lower shell cover (2).

4. The electrical integration system for an aircraft battery system according to claim 2, characterized in that: It also includes an electrical connector (15), through which the plurality of contactor modules (12) are connected in parallel with the fuse module (14).

5. The electrical integration system for an aircraft battery system according to claim 2, characterized in that: The side surface of the lower shell cover (2) comprises a plurality of openings, and the wiring harness portion passes through the openings and is respectively connected to the current sensing module (11), the contactor module (12), the pre-charging module (13) and the insurance module (14).

6. The electrical integration system for an aircraft battery system according to claim 1, characterized in that: The bottom edge of the lower shell cover (2) further comprises a fixing portion (20), and the fixing portion (20) is used for connecting to an aircraft.

7. The electrical integration system for an aircraft battery system according to claim 1, characterized in that: The operating information includes at least the voltage and temperature of the battery cells in the battery pack.

8. The electrical integration system for an aircraft battery system according to claim 1, characterized in that: The pre-charging module (13) comprises a pre-charging contactor (131) and a pre-charging resistor (132).

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