Battery cell module device suitable for aircraft structure

Abstract

The utility model discloses a battery cell module device suitable for an aircraft structure, which comprises battery cells and a module, the battery cells are arranged in the module along the circumference of the inside of the module, the module adopts a circular structure, the module comprises a module inner hole and a module appearance, the module inner hole is positioned in the middle of the module appearance, and the module inner hole is positioned in the middle of the module appearance. The appearance of the module is of a shell structure of the module, the module is formed by connecting a plurality of battery cells in parallel, the shell structure comprises an outer circular shell and an inner circular shell, the outer circular shell is made of carbon fibers, the inner circular shell is mainly made of aluminum alloy, and heat-conducting glue and foam are arranged between the shell structure and the battery cells for filling. The battery cell device is utilized to increase the energy density of the battery, the weight of an airplane body can be reduced when the energy density is increased, meanwhile, the cruising ability can be improved, the heat-conducting glue and the foam are arranged between the shell structure and the battery cell, the heat dissipation effect of the module is improved, the thermal runaway risk of the module is greatly reduced after the heat dissipation effect is improved, and the service life of the module is prolonged. And the safety is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of battery core modules, and in particular to a battery core module device suitable for aircraft structures. Background Art

[0002] With the rapid development of the aviation industry, aircraft structural materials are gradually developing towards lightweight, high strength and high durability. As the main energy source of aircraft, the performance and structure of batteries directly affect the safety and economy of aircraft.

[0003] Traditional aircraft batteries are heavy, bulky, have low charging efficiency and poor heat dissipation performance, and therefore cannot meet the needs of modern aircraft.

[0004] Chinese Patent CN116154357A Publication Date: May 23, 2023 Discloses a combined thermal management system for power batteries for electric aircraft, including: a pair of water-cooled plates, with water inlets and water outlets at both ends; battery cells, spaced and arranged between the pair of water-cooled plates; solid-solid phase change heat storage plates, clamped on both sides of each of the battery cells. The present invention has the following advantages and effects: The battery module and the refrigeration system of the aircraft are designed separately to solve the problem of the electric aircraft being overweight due to the heavy water cooling unit. During the flight phase of the aircraft, a solid-solid phase change heat storage plate is used to absorb the heat generated by the battery cell, and during the ground phase, a water-cooled circulation cooling method is used to absorb the heat generated by the battery cell, which can effectively solve the problem of heat dissipation of the battery cell at different stages of the aircraft. However, the above patent does not solve the problems of heavy weight, large volume, and low charging efficiency.

[0005] Chinese patent CN220341316U Publication date: January 12, 2023 discloses a composite electric aircraft power battery heat dissipation structure, including a battery module, the battery module has a built-in battery cell, the battery module includes an upper isolation plate and a lower isolation plate, the upper isolation plate and the lower isolation plate are provided with a recessed structure matching the battery cell at the position of the battery cell bar, the upper isolation plate, the battery cell and the lower isolation plate are locked and fixed by a supporting structure; the battery module also includes a water-cooled heat dissipation structure and a heat conductive sheet, by arranging a heat conductive sheet in the recessed structure, the heat generated by the battery cell when working is accelerated by the heat conductive sheet to the water-cooled heat dissipation structure, and then the heat generated by the bar and the battery cell is exported by the circulating coolant inside the water-cooled heat dissipation structure, which can solve the problem of excessive temperature rise of the battery cell and the bar during high-rate charging and discharging. However, when encountering special environments, it is difficult to ensure stability and safety.

[0006] The existing technology adopts a new type of battery module device with a modular design, which can flexibly form battery packs of various shapes and capacities. It uses an efficient cooling system to ensure that the battery can work stably in a high temperature environment.

[0007] However, existing battery cell module devices also have some problems. The battery is prone to explosion when impacted by external force, posing a safety hazard. Given the special environment of aircraft, how to ensure the stability and safety of the battery is a challenge. The battery life is relatively short and requires regular replacement and maintenance, which increases operating costs. Utility Model Content

[0008] In order to solve the technical problems of low energy density and worse heat dissipation of battery packs, a battery cell module device suitable for aircraft structure is provided.

[0009] A battery cell module device suitable for aircraft structure, characterized by comprising: a battery cell unit and a module;

[0010] The battery cell unit is arranged inside the module;

[0011] The battery cell units are arranged along a circumference of the inside of the module;

[0012] The module adopts a circular structure;

[0013] The module includes a module inner hole and a module outer shape;

[0014] The inner hole of the module is located in the middle of the module shape;

[0015] The module shape is the outer shell structure of the module.

[0016] Preferably, the module is composed of multiple battery cell units connected in parallel.

[0017] Preferably, the battery cell units are divided into two layers; the battery cell units are evenly arranged inside the module.

[0018] Preferably, a wire hole is provided inside the battery cell unit; and extra space is left outside the battery cell unit to facilitate heat dissipation of the module.

[0019] Preferably, the battery cell unit structure is fixed by battery cell unit stacking.

[0020] Preferably, the outer shell structure comprises an outer circular shell and an inner circular shell; the outer circular shell is made of carbon fiber and the inner circular shell is mainly made of aluminum alloy.

[0021] Preferably, thermally conductive glue and foam are provided between the shell structure and the battery core unit for filling.

[0022] Preferably, the outer cylindrical shell adopts a thin-walled cylindrical structure; the outer cylindrical shell is used to accommodate the internal components of the battery cell unit, namely, the positive electrode, the negative electrode and the electrolyte.

[0023] Preferably, the inner cylindrical shell is composed of a plurality of thin-walled cylinders stacked together, thereby providing overall structural strength to the battery cell unit.

[0024] Preferably, the overall structure of the module has a diameter of 145mm-150mm, an inner diameter of 48mm-52mm, and a height of 78mm-82mm.

[0025] Compared with the prior art, the utility model has the following advantages:

[0026] 1. The utility model discloses a battery module device suitable for aircraft structure, which increases the energy density of the battery by using the battery unit device. When the energy density is increased, the weight of the aircraft body will be reduced, and the endurance can be improved at the same time.

[0027] 2. The utility model is a battery module device suitable for aircraft structure, which increases the heat dissipation effect of the module by arranging thermal conductive glue and foam between the outer shell structure and the battery cell unit. After the heat dissipation effect is increased, the risk of thermal runaway of the module is greatly reduced, thereby improving safety.

[0028] The above is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application so that it can be implemented in accordance with the contents of the specification, and to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the following is a detailed description of the preferred embodiments of the present application in conjunction with the accompanying drawings as follows.

[0029] Based on the detailed description of the specific embodiments of the present application in combination with the accompanying drawings below, those skilled in the art will become more aware of the above and other objects, advantages and features of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can also be obtained based on these drawings without creative work. In all drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual scale.

[0031] Figure 1 It is a schematic diagram of a battery module device suitable for aircraft structure of the utility model;

[0032] Figure 2 This is a module cross-sectional view of a battery module device suitable for aircraft structure according to the utility model;

[0033] Figure numerals: 1. battery cell unit; 2. module inner hole; 3. module outer shape. DETAILED DESCRIPTION

[0034] To make the purpose, technical scheme and advantages of the embodiment of the present application clearer, the technical scheme in the embodiment of the present application will be clearly and completely described below in conjunction with the drawings in the embodiment of the present application. Obviously, the described embodiment is a part of the embodiment of the present application, rather than all the embodiments. In the following description, specific details such as specific configurations and components are provided only to help fully understand the embodiments of the present application. Therefore, it should be clear to those skilled in the art that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present application. In addition, for clarity and brevity, the description of known functions and structures is omitted in the embodiment. It should be understood that "one embodiment" or "this embodiment" mentioned throughout the specification means that the specific features, structures or characteristics related to the embodiment are included in at least one embodiment of the present application. Therefore, "one embodiment" or "this embodiment" appearing in various places throughout the specification may not necessarily refer to the same embodiment. In addition, these specific features, structures or characteristics can be combined in one or more embodiments in any suitable manner.

[0035] In addition, the present application may repeat reference numerals and / or letters in different examples. This repetition is for the purpose of simplicity and clarity, and does not in itself indicate the relationship between the various embodiments and / or settings discussed.

[0036] The term "and / or" in this article is only a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can mean: A exists alone, B exists alone, and A and B exist at the same time. The term " / and" in this article describes another type of association relationship between associated objects, indicating that there can be two relationships. For example, A / and B can mean: A exists alone, and A and B exist alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0037] It should also be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusions.

[0038] Example 1

[0039] This embodiment mainly introduces a main structure of a battery cell module device suitable for aircraft structure.

[0040] A battery cell module device suitable for aircraft structure, characterized by comprising: a battery cell unit 1, a module;

[0041] The battery cell unit 1 is arranged inside the module;

[0042] The battery cell units 1 are arranged along a circumference of the inside of the module;

[0043] The module adopts a circular structure;

[0044] The module comprises a module inner hole 2 and a module outer shape 3;

[0045] The module inner hole 2 is located in the middle of the module outer shape 3;

[0046] The module shape 3 is the outer shell structure of the module.

[0047] Furthermore, the module is composed of multiple battery cell units 1 connected in parallel.

[0048] Furthermore, the battery cell units 1 are divided into two layers; the battery cell units 1 are evenly arranged inside the module.

[0049] Furthermore, a wire hole is provided inside the battery cell unit 1 ; and extra space is left outside the battery cell unit 1 to facilitate heat dissipation of the module.

[0050] Furthermore, the structure of the battery cell unit 1 is fixed by stacking the battery cell unit 1 .

[0051] Furthermore, the outer shell structure includes an outer circular shell and an inner circular shell; the outer circular shell is made of carbon fiber and the inner circular shell is mainly made of aluminum alloy.

[0052] Furthermore, thermally conductive glue and foam are provided between the shell structure and the battery core unit 1 for filling.

[0053] Furthermore, the outer cylindrical shell adopts a thin-walled cylindrical structure; the outer cylindrical shell is used to accommodate the internal components of the battery cell unit 1, namely, the positive electrode, the negative electrode and the electrolyte.

[0054] Furthermore, the inner cylindrical shell is composed of a plurality of thin-walled cylinders stacked together, which provides overall structural strength for the battery cell unit 1 .

[0055] Furthermore, the overall structure of the module has a diameter of 145mm-150mm, an inner diameter of 48mm-52mm, and a height of 78mm-82mm.

[0056] The present embodiment mainly relates to a battery cell module device suitable for aircraft structure. The battery cell device is used to increase the energy density of the battery. When the energy density is increased, the weight of the aircraft body will be reduced, and the endurance can be improved at the same time.

[0057] Example 2

[0058] This embodiment is based on the above-mentioned embodiment 1 and mainly introduces a battery cell device suitable for aircraft structure.

[0059] The battery cells are divided into two layers and evenly arranged inside the module, which can fully utilize the space while ensuring the stability and safety of the battery pack;

[0060] The battery cell unit is designed with special wire holes inside, which can be directly connected to the external battery management system, simplifying the line connection of the battery pack; the wire holes inside the battery cell also facilitate the maintenance and repair of the battery pack, improving the reliability and stability of the entire system;

[0061] We have also designed a special inner arm of the battery cell inside the battery cell. The inner arm inside the battery cell leaves a certain space, which can effectively help the battery cell dissipate heat, effectively improve the heat dissipation efficiency of the battery pack, and extend the life of the battery pack.

[0062] Example 3

[0063] This embodiment is based on the above-mentioned embodiment 1, and mainly introduces a battery cell outer circular shell and an inner circular shell of a battery mold package device suitable for aircraft structure.

[0064] The outer cylindrical shell is usually a thin-walled cylinder for accommodating the internal components of the battery cell, the positive electrode, the negative electrode and the electrolyte;

[0065] The inner cylindrical shell is the core part of the battery cell, which is usually composed of multiple thin-walled cylinders stacked together to provide the overall structural strength of the battery cell.

[0066] The outer cylindrical shell and the inner cylindrical shell of the battery cell are usually connected by hot pressing; the outer cylindrical shell and the inner cylindrical shell are heated and pressurized to combine the two metal shells together to ensure the strength and sealing of the connection part.

[0067] The structure of the outer circular shell and the inner circular shell is designed to have different shapes and sizes to adapt to different types of battery cells. The cylindrical outer circular shell adopts a hollow cylindrical structure. As for the inner circular shell, it may be designed to have different shapes and sizes to provide sufficient space to accommodate the internal components of the battery cell and ensure the overall performance and safety of the battery cell.

[0068] The above description is only the preferred embodiment of the utility model, which does not limit the protection scope of the utility model. For those skilled in the art, the utility model can be modified and varied in various ways. Any changes, modifications, substitutions, integrations and parameter changes to these embodiments within the spirit and principle of the utility model through conventional substitutions or capable of achieving the same functions without departing from the principles and spirit of the utility model shall fall within the protection scope of the utility model.

Claims

1. A battery module device suitable for aircraft structure, characterized in that: include: Battery cell unit (1), module; The battery cell unit (1) is arranged inside the module; The battery cell units (1) are arranged along a circumference of the interior of the module; The module adopts a circular structure; The module comprises a module inner hole (2) and a module outer shape (3); The module inner hole (2) is located in the middle of the module outer shape (3); The module shape (3) is the outer shell structure of the module.

2. The battery module device suitable for aircraft structure according to claim 1, characterized in that: The module is composed of multiple battery core units (1) connected in parallel.

3. The battery module device suitable for aircraft structure according to claim 2, characterized in that: The battery cell units (1) are divided into two layers; the battery cell units (1) are evenly arranged inside the module.

4. The battery module device suitable for aircraft structure according to claim 3, characterized in that: A wire hole is arranged inside the battery cell unit (1); and extra space is left outside the battery cell unit (1) to facilitate heat dissipation of the module.

5. The battery module device suitable for aircraft structure according to claim 4, characterized in that: The battery cell unit (1) structure is fixed by the battery cell unit (1) stack.

6. The battery module device suitable for aircraft structure according to claim 5, characterized in that: The shell structure comprises an outer circular shell and an inner circular shell; the outer circular shell is made of carbon fiber and the inner circular shell is mainly made of aluminum alloy.

7. The battery module device suitable for aircraft structure according to claim 6, characterized in that: Thermally conductive glue and foam are provided between the shell structure and the battery core unit (1) for filling.

8. The battery module device suitable for aircraft structure according to claim 7, characterized in that: The outer cylindrical shell adopts a thin-walled cylindrical structure; the outer cylindrical shell is used to accommodate the internal components of the battery cell unit (1), the positive electrode, the negative electrode and the electrolyte.

9. The battery module device suitable for aircraft structure according to claim 7, characterized in that: The inner cylindrical shell is composed of a plurality of thin-walled cylinders stacked together, providing overall structural strength to the battery cell unit (1).

10. The battery module device suitable for aircraft structure according to claim 1, characterized in that: The overall structure of the module is 145mm-150mm in diameter, 48mm-52mm in inner diameter, and 78mm-82mm in height.

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