A modular aviation power battery system

Abstract

The present invention relates to the field of aviation technology, and in particular to a modular aviation power battery system. Its technical solution includes: a battery housing, a mounting plate and an aircraft body. The mounting plate is fixedly installed inside the battery housing, and the surface of the mounting plate is respectively provided with a power module and a collection module. A cover plate is installed on the surface of the battery housing at one end of the mounting plate, and a display screen is fixedly installed on the surface of the cover plate. The output of the power module and the collection module of the present invention adopts a quick-change connector mode, and the weight of each module is controlled below 30kg, which can be installed and replaced more conveniently. In addition, by adopting a series or parallel connection, the entire system can realize two to more than ten power circuits, realize functional redundancy, and improve safety performance. The small module has a lower requirement for a regular large-size space, and can be installed in many places during flight, fully meeting the requirements of the fragmented space of the aircraft and optimizing the use process.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to a modular aviation power battery system. Background Art

[0002] Aviation is a complex and strategically significant human activity, referring to the flight activities of aircraft in the Earth's atmosphere. Aircraft engaged in flight activities, also known as aircraft, are divided into two categories: lighter-than-air aircraft and heavier-than-air aircraft. The former, such as balloons and airships, use the static buoyancy of air to take off, while the latter, such as airplanes and helicopters, use aerodynamic force to take off. In the field of aviation technology, power battery systems are needed.

[0003] After searching, the patent announcement number CN209183599U discloses an aviation power battery pack system, which includes a storage shell. The storage shell is a cylindrical structure, one end is closed, and the other end is provided with an opening. An aviation power battery is arranged in the storage shell. A negative electrode trigger mechanism is arranged at the closed end of the storage shell. The open end of the storage shell is connected with the shell cover, and a positive electrode trigger mechanism is arranged in the shell cover.

[0004] The defects of existing modular aviation power battery systems are:

[0005] 1. The existing modular aviation power battery system still adopts a similar architecture to the automotive power battery system. Due to the requirements of flight and load, the power system requires both high power and high specific energy. However, most of the existing power batteries adopt high specific energy or high power. There is no power battery that meets both requirements. Moreover, most of them are heavy, making inspection and maintenance difficult.

[0006] 2. The existing modular aviation power battery system is relatively large in size, and there is no large-scale installation space on the aircraft, which greatly reduces the utilization of space. In addition, the power circuit is relatively simple, with less redundancy and low safety performance. Summary of the invention

[0007] The object of the present invention is to provide a modular aviation power battery system to solve the problems raised in the above background technology.

[0008] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a modular aviation power battery system, comprising a battery housing, a mounting plate and an aircraft body, wherein the interior of the aircraft body is provided with a battery housing, a mounting plate is fixedly installed inside the battery housing, a power module and a collection module are respectively arranged on the surface of the mounting plate, a cover plate is installed on the surface of the battery housing at one end of the mounting plate, a display screen is fixedly installed on the surface of the cover plate, and a protective coating layer is arranged on the periphery of the battery housing.

[0009] This device splits the functions of the power battery system and implements them on different components. First, the power distribution bus is integrated with the power distribution part of the aircraft, and only the power module and the acquisition module are retained to simplify the functions. The voltage and temperature of the device are collected in real time through the acquisition module, and the collected data are displayed on the display screen to facilitate observation by the staff. The charging control part is integrated with the charging cabinet or the battery swap cabinet. The charging cabinet or the battery swap cabinet can realize the functions of overall charging and single-cell charging, so that the discharge and charging of the power battery system can be separated, and centralized battery charging maintenance can be realized to improve safety performance. This device adopts a small module method, which includes a power module and an acquisition module, and the output of the power module and the acquisition module adopts a quick-change connector mode. The weight of each module is controlled below 30kg, which can be installed and replaced more conveniently. In addition, by adopting a series or parallel method, the entire system can realize two to more than ten power circuits, realize functional redundancy, and improve safety performance. The small module has a lower requirement for regular large-size space and can be installed in many places during flight, fully meeting the requirements of fragmented space of the aircraft.

[0010] Preferably, an inspection bolt is installed between the cover plate and the battery housing, and the surface of the inspection bolt is coated with an anti-oxidation coating. The cover plate can be removed by disassembling the inspection bolt, which is convenient for the staff to carry out disassembly and maintenance work, and the anti-oxidation coating can prevent the inspection bolt from rusting and damage.

[0011] Preferably, a nameplate is fixedly mounted on the surface of the other end of the battery housing, and bolts are fixedly mounted between the nameplate and the battery housing. The nameplate can be convenient for staff to check the model and specifications of the device, and the nameplate can be mounted on the battery housing by bolts to increase the stability of the nameplate.

[0012] Preferably, a buckle is installed on one side of the battery shell, and a latch is arranged inside the buckle. The buckle can be loosened by loosening the latch, so that the staff can disassemble the battery shell for disassembly and maintenance.

[0013] Preferably, the surface of the other end of the battery housing is provided with heat dissipation holes, and dustproof nets are provided inside the heat dissipation holes. The heat dissipation holes can increase the heat dissipation effect of the battery housing, and the dustproof nets can prevent dust from entering the battery housing through the heat dissipation holes.

[0014] Preferably, a first protective layer is disposed inside the protective coating layer, and a waterproof layer is disposed inside the first protective layer. The first protective layer can provide protection for the battery housing, and the waterproof layer can provide a waterproof effect for the battery housing.

[0015] Preferably, a second protective layer is provided inside the protective coating layer, and an antirust layer is provided inside the second protective layer. The second protective layer can provide protection for the battery shell, and the antirust layer can provide an antirust effect for the battery shell.

[0016] Preferably, a third protective layer is provided inside the protective coating layer, and a flame retardant layer is provided inside the third protective layer. The third protective layer can provide protection for the battery shell, and the flame retardant layer can provide heat insulation and flame retardant effects for the battery shell.

[0017] Preferably, a fourth protective layer is provided inside the protective coating layer, and an insulating layer is provided inside the fourth protective layer. The fourth protective layer can provide protection for the battery shell, and the insulating layer can provide insulation effect for the battery shell, thereby increasing the protective effect of the battery shell.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. By arranging a power module and a collection module on the surface of the mounting plate respectively, and fixing a display screen on the surface of the cover plate, the device splits the functions of the power battery system and implements them on different components. First, the power distribution bus part is integrated with the power distribution part of the aircraft, and only the power module and the collection module are retained to simplify the functions. The voltage and temperature of the device are collected in real time through the collection module, and the collected data is displayed on the display screen to facilitate observation by the staff. The charging control part is integrated with the charging cabinet or the battery swap cabinet. The charging cabinet or the battery swap cabinet can realize the functions of overall charging and single-cell charging, so that the discharge and charging of the power battery system can be separated, and centralized battery charging maintenance can be realized, safety performance can be improved, and the use process can be optimized.

[0020] 2. A mounting plate is fixedly installed inside the battery casing, and a power module and a collection module are respectively arranged on the surface of the mounting plate. The device adopts a small module method, and the small module includes a power module and a collection module. The output of the power module and the collection module adopts a quick-change connector mode. The weight of each module is controlled below 30kg, which can be installed and replaced more conveniently. In addition, by adopting a series or parallel connection method, the entire system can realize two to more than ten power circuits, achieve functional redundancy, and improve safety performance. The small module has a lower requirement for regular large-size space and can be installed in many places during flight, fully meeting the requirements of fragmented space of the aircraft and optimizing the use process. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A perspective view of the present invention;

[0022] Figure 2 is a side view of the present invention;

[0023] Figure 3 It is a rear view of the present invention;

[0024] Figure 4 It is a schematic diagram of the internal structure of the present invention;

[0025] Figure 5 It is a front view of the present invention;

[0026] Figure 6 It is a schematic diagram of the local structure of the protective coating layer of the present invention;

[0027] Figure 7 It is a schematic diagram of the local structure of the aircraft body of the present invention.

[0028] In the figure: 1. Battery casing; 2. Collection module; 3. Mounting plate; 4. Power module; 5. Cover plate; 6. Protective coating layer; 7. Inspection plug; 8. Display screen; 9. Nameplate; 10. First protective layer; 1001. Waterproof layer; 11. Second protective layer; 1101. Anti-rust layer; 12. Third protective layer; 1201. Flame retardant layer; 13. Fourth protective layer; 1301. Insulating layer; 14. Buckle; 15. Heat dissipation hole; 16. Aircraft body. DETAILED DESCRIPTION

[0029] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0030] Embodiment 1

[0031] like Figure 1 , 4 As shown in Figures 5 and 7, a modular aviation power battery system proposed by the present invention comprises a battery casing 1, a mounting plate 3 and an aircraft body 16, the interior of the aircraft body 16 is provided with a battery casing 1, the interior of the battery casing 1 is fixedly provided with a mounting plate 3, the surfaces of the mounting plate 3 are respectively provided with a power module 4 and a collection module 2, a cover plate 5 is installed on the surface of the battery casing 1 at one end of the mounting plate 3, a display screen 8 is fixedly installed on the surface of the cover plate 5, a protective coating layer 6 is arranged on the periphery of the battery casing 1, an inspection plug 7 is installed between the cover plate 5 and the battery casing 1, and the surface of the inspection plug 7 is coated with an anti-oxidation coating, a buckle 14 is installed on one side of the battery casing 1, and a bolt is arranged inside the buckle 14.

[0032] The working principle of the modular aviation power battery system based on Example 1 is: this device splits the functions of the power battery system and implements them on different components. First, the power distribution bus part is integrated with the power distribution part of the aircraft, and only the power module 4 and the acquisition module 2 are retained to simplify the functions. The voltage and temperature of the device are collected in real time through the acquisition module 2, and the collected data are displayed on the display screen 8 to facilitate observation by the staff, and the charging control part is integrated with the charging cabinet or the battery swap cabinet. The charging cabinet or the battery swap cabinet can realize the functions of overall charging and single-cell charging, so that the discharge and charging of the power battery system can be separated, and centralized battery charging maintenance can be realized, safety performance can be improved, and the use process can be optimized. The device adopts a small module method, and the small module includes a power module 4 and a collection module 2, and the power module The output of block 4 and acquisition module 2 adopts a quick-change connector mode. The weight of each module is controlled below 30kg, which can be installed and replaced more conveniently. In addition, by adopting a series or parallel connection, the entire system can realize two to more than ten power circuits, achieve functional redundancy, and improve safety performance. Small modules have lower requirements for regular large-size spaces and can be installed in many places during flight, fully meeting the requirements of fragmented aircraft space and optimizing the use process. The protective coating layer 6 can provide protection for the battery casing 1, and the cover plate 5 can be removed by removing the maintenance bolt 7, which is convenient for the staff to carry out disassembly and maintenance. The anti-oxidation coating can prevent the maintenance bolt 7 from rusting and damage, and the buckle 14 can be loosened by loosening the bolt, which is convenient for the staff to disassemble the battery casing 1 for disassembly and maintenance, thereby optimizing the use process.

[0033] Embodiment 2

[0034] like Figure 2 , 3 6, a modular aviation power battery system proposed by the present invention, compared with the first embodiment, this embodiment also includes: a nameplate 9 is fixedly installed on the surface of the other end of the battery casing 1, and bolts are fixedly installed between the nameplate 9 and the battery casing 1, the surface of the other end of the battery casing 1 is provided with heat dissipation holes 15, and the inside of the heat dissipation holes 15 is provided with dustproof nets, the inside of the protective coating layer 6 is provided with a first protective layer 10, and the inside of the first protective layer 10 is provided with a waterproof layer 1001, the inside of the protective coating layer 6 is provided with a second protective layer 11, and the inside of the second protective layer 11 is provided with an anti-rust layer 1101, the inside of the protective coating layer 6 is provided with a third protective layer 12, and the inside of the third protective layer 12 is provided with a flame retardant layer 1201, the inside of the protective coating layer 6 is provided with a fourth protective layer 13, and the inside of the fourth protective layer 13 is provided with an insulating layer 1301.

[0035] In this embodiment, the nameplate 9 can facilitate the staff to check the model and specifications of the device, the nameplate 9 can be installed on the battery casing 1 by bolts to increase the stability of the nameplate 9, the heat dissipation effect of the battery casing 1 can be increased by the heat dissipation holes 15, and the dust-proof net can prevent dust from entering the battery casing 1 through the heat dissipation holes 15. The first protective layer 10 can provide protection for the battery casing 1, the waterproof layer 1001 can provide a waterproof effect for the battery casing 1, the second protective layer 11 can provide protection for the battery casing 1, the anti-rust layer 1101 can provide a rust-proof effect for the battery casing 1, the third protective layer 12 can provide protection for the battery casing 1, the flame retardant layer 1201 can provide a heat insulation and flame retardant effect for the battery casing 1, the fourth protective layer 13 can provide protection for the battery casing 1, and the insulating layer 1301 can provide an insulating effect for the battery casing 1, thereby increasing the protective effect of the battery casing 1.

[0036] The above-mentioned specific embodiments are only several preferred embodiments of the present invention. Based on the technical solutions of the present invention and the relevant inspirations of the above-mentioned embodiments, those skilled in the art can make various alternative improvements and combinations to the above-mentioned specific embodiments.

Claims

1. A modular aviation power battery system, comprising a battery housing (1), a mounting plate (3) and an aircraft body (16), characterized in that: The interior of the aircraft body (16) is provided with a battery housing (1), a mounting plate (3) is fixedly mounted inside the battery housing (1), a power module (4) and a collection module (2) are respectively mounted on the surface of the mounting plate (3), a cover plate (5) is mounted on the surface of the battery housing (1) at one end of the mounting plate (3), a display screen (8) is fixedly mounted on the surface of the cover plate (5), and a protective coating layer (6) is arranged on the periphery of the battery housing (1), wherein the outputs of the power module (4) and the collection module (2) adopt a quick-change connector mode, the weight of each module is controlled to be less than 30 kg, and a two-way to ten-way or more power circuit is realized in a series or parallel manner; The power distribution bus portion of the system is integrated with the power distribution portion of the aircraft, and only the power module (4) and the acquisition module (2) are retained, and the voltage and temperature of the device are collected in real time through the acquisition module (2); The system integrates the charging control part with the charging cabinet or the battery swapping cabinet, and the charging cabinet or the battery swapping cabinet can realize the functions of overall charging and single-cell charging, thereby realizing the separation of discharge and charging of the power battery system; A first protective layer (10) is arranged inside the protective coating layer (6), and a waterproof layer (1001) is arranged inside the first protective layer (10); A third protective layer (12) is provided inside the protective coating layer (6), and a flame retardant layer (1201) is provided inside the third protective layer (12); A second protective layer (11) is provided inside the protective coating layer (6), and an anti-rust layer (1101) is provided inside the second protective layer (11); A fourth protective layer (13) is provided inside the protective coating layer (6), and an insulating layer (1301) is provided inside the fourth protective layer (13).

2. A modular aviation power battery system according to claim 1, characterized in that: An inspection plug (7) is installed between the cover plate (5) and the battery housing (1), and the surface of the inspection plug (7) is coated with an anti-oxidation coating.

3. The modular aviation power battery system according to claim 1, characterized in that: A nameplate (9) is fixedly mounted on the surface of the other end of the battery housing (1), and bolts are fixedly mounted between the nameplate (9) and the battery housing (1).

4. The modular aviation power battery system according to claim 1, characterized in that: A buckle (14) is installed on one side of the battery housing (1), and a latch is arranged inside the buckle (14).

5. The modular aviation power battery system according to claim 1, characterized in that: The surface of the other end of the battery housing (1) is provided with heat dissipation holes (15), and dustproof nets are provided inside the heat dissipation holes (15).

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