Battery pack for aircraft

Abstract

The invention provides a battery pack for an aircraft, the battery pack comprises a battery box body, a battery module, a liquid cooling plate, a control panel, a relay, a fuse and a heat dissipation system, the battery module, the control panel, the relay and the fuse are all arranged in the battery box body, and the liquid cooling plate is attached to the outer surface of the battery module. According to the battery pack for the aircraft, the battery module and the control modules are integrated, independent self-inspection and control of the battery pack are achieved, the control modules are distributed on the two sides of the module, the gravity center of the battery pack is centered, the battery pack better adapts to the complex working environment of the aircraft, and pouring sealant in the module effectively reduces external impact and vibration. And meanwhile, the separation control module realizes division of functional areas, and meanwhile, the battery pack shell is decomposed into a battery box body and a rear mounting plate for mounting the control module, so that the maintenance cost of the battery pack is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a battery pack for an aircraft. BACKGROUND

[0002] The aircraft on the market generally adopts a pure electrification platform, which takes a power battery as the only energy storage component. Since there is a direct positive correlation between the endurance mileage of the aircraft and the energy density of the power battery, by reducing the energy consumption of other systems except the power system, the endurance mileage anxiety problem faced by the aircraft can be significantly reduced.

[0003] The current traditional battery pack has the following problems: first, the module integration is not high, and maintenance is difficult. Second, the cells are generally vertically stacked, and the space utilization rate in the battery pack is low.

[0004] Based on the above problems, the present application is born. SUMMARY

[0005] Technical problems to be solved In view of the defects of the prior art, the present application provides a battery pack for an aircraft, which solves the problems proposed in the background art.

[0006] Technical scheme In order to achieve the above purpose, the present application is realized by the following technical scheme: a battery pack for an aircraft, comprising a battery box, a battery module, a liquid cooling plate, a control panel, a relay, a fuse, the battery module, the control panel, the relay and the fuse are arranged in the battery box, the liquid cooling plate is arranged in the battery box in a serpentine reciprocating manner, and the battery module is arranged in the liquid cooling plate.

[0007] Preferably, the battery box is L-shaped, and the front end of the battery box is provided with a front mounting plate and a rear mounting plate.

[0008] Preferably, the battery module is horizontally placed in the battery box.

[0009] Preferably, the control panel, the relay and the fuse are arranged on both sides of the battery module close to the front mounting plate and the rear mounting plate. Advantages

[0010] The present application provides a battery pack for an aircraft. It has the following advantages: The battery pack for the aircraft integrates the battery module and the control module, realizes the independent inspection and control of the battery pack, distributes the control module on both sides of the module, realizes the centering of the gravity center of the battery pack to better adapt to the complex working environment of the aircraft, and effectively reduces the external impact and vibration by filling the glue in the module. BRIEF DESCRIPTION OF DRAWINGS

[0011] Figure 1 is a whole one side axonometric exploded view of the application; Figure 2 is a whole another side axonometric exploded view of the application.

[0012] In the figure: 1 battery box, 2 battery module, 3 liquid cooling plate, 6 control board, 7 relay, 8 fuse, 9 rear mounting plate, 10 front mounting plate. DETAILED DESCRIPTION

[0013] The embodiment of the application provides a battery pack for an aircraft, as shown in Figure 1 and Figure 2 , comprising a battery box 1, a battery module 2, a liquid cooling plate 3, a control board 6, a relay 7 and a fuse 8.

[0014] As shown in Figure 1 and Figure 2 , the battery module 2, the control board 6, the relay 7 and the fuse 8 are arranged in the battery box 1. The total positive output end of the battery module 2 is firstly connected in series with the fuse 8 to prevent damage to components when the main circuit is short-circuited or overcurrent. The output end of the fuse 8 is connected to the input end of the relay 7, and the output end of the relay 7 is connected to the high-voltage output interface of the battery pack of the battery module 2.

[0015] The battery box 1 has an L-shaped appearance, and the front end bending part of the battery box 1 and the rear end are respectively provided with a front mounting plate 10 and a rear mounting plate 9. The front mounting plate 10 and the rear mounting plate 9 are detachable.

[0016] The control board 6, the relay 7 and the fuse 8 are respectively arranged on both sides of the battery module 2 close to the front mounting plate 10 and the rear mounting plate 9. The control board 6 is mounted on the rear mounting plate 9.

[0017] The battery module 2 is integrated with the control module to realize the self-inspection and control of the battery pack, the control module is distributed on both sides of the module to realize the centering of the gravity center of the battery pack and better adapt to the complex working environment of the aircraft, the potting glue in the module effectively reduces the external impact and vibration. At the same time, the separation of the control module realizes the division of the functional area, and the battery pack shell is divided into a battery box 1 and a rear mounting plate 9 for mounting the control module, thereby reducing the maintenance cost of the battery pack. The control module is arranged closer to the corresponding interface of the control element on the module to reduce the wiring distance, effectively reduce the weight of the battery pack, improve the grouping efficiency, and the division of the functional area improves the maintenance and detection efficiency.

[0018] As shown in Figure 1 The liquid cooling plate 3 is arranged in a serpentine reciprocating manner in the battery box 1, the liquid cooling plate 3 is a flow channel, and the plurality of battery cells of the battery module 2 are respectively placed in the middle gap of the liquid cooling plate 3.

[0019] The battery module 2 is horizontally laid in the battery box 1. The battery module 2 is provided with a plurality of groups arranged in a horizontal manner, the battery cells are arranged in a horizontal manner, the Z-direction size is reasonably utilized, the space utilization is improved, and the small aircraft and other scenes with high requirements for external size are better adapted. At the same time, the potting technology is adopted, the potting glue is used to ensure the gap between the battery cells and the liquid cooling plate 3, the collision and damage caused by vibration are avoided, the aircraft working condition with large vibration is better adapted, and the safety of the battery is improved.

[0020] Although the embodiments of the present application have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to the embodiments without departing from the principles and spirits of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A battery pack for an aircraft, characterized by: Including battery box (1), battery module (2), liquid cooling plate (3), control panel (6), relay (7), fuse (8), the control panel (6), relay (7), fuse (8) are all arranged in battery box (1), the liquid cooling plate (3) is arranged in battery box (1) in serpentine reciprocating type, the several electric core of battery module (2) is placed in the middle gap of liquid cooling plate (3) respectively.

2. The battery pack for an aerial vehicle of claim 1, wherein: The appearance of battery box (1) is L-shaped, and the front mounting plate (10) and the rear mounting plate (9) are respectively arranged at the front end bending part and the rear end of battery box (1).

3. The battery pack for an aircraft of claim 2, wherein: The battery module (2) is horizontally laid in the battery box (1).

4. The battery pack for an aerial vehicle of claim 3, wherein: The control panel (6), the relay (7) and the fuse (8) are respectively arranged at the two sides of the battery module (2) close to the front mounting plate (10) and the rear mounting plate (9).

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