Battery pack for electric aircraft

Abstract

The utility model discloses a battery pack for an electric aircraft, which comprises a shell integrally arranged in a hollow rectangular shape; the battery cells are arranged in the shell side by side; the fixing plate is arranged in a C shape and is provided with an opening, and the battery cell is embedded into the fixing plate; the cooling fins are integrally formed and vertically arranged at the opening positions of the two sides of the fixing plate. Compared with the prior art, the battery pack has the following advantages and effects: by arranging the mounting structure integrating the fixing plate and the radiating fins, the battery cell can be fixed, the radiating of the battery cell can be ensured, the battery pack is fixed, the structure number and the structure weight are reduced, and meanwhile, the heat transfer efficiency is high and the radiating efficiency is improved due to the integral forming arrangement.

Description

Technical Field

[0001] The utility model relates to the technical field of batteries, and in particular to a battery pack for an electric aircraft. Background Art

[0002] Electric aircraft refers to aircraft that are powered by electric motors rather than internal combustion engines. The power sources include fuel cells, solar cells, supercapacitors, wireless energy transmission or other types of batteries. With the continuous popularization and development of lithium-ion batteries, in order to improve the life of battery packs, the research on heat dissipation of battery packs has gradually become a research and development hotspot.

[0003] Existing aviation battery packs all fix the battery soft pack in a C-shaped plate, screw L-shaped angle pieces on the upper and lower sides as heat dissipation fins, and then dissipate heat through air cooling. This heat dissipation structure has many structural parts, the battery pack is heavy, the energy density is relatively small, the heat transfer effect is poor, and the heat dissipation efficiency is relatively low, which needs to be improved. Utility Model Content

[0004] In view of the deficiencies in the prior art, the purpose of the utility model is to provide a battery pack for an electric aircraft, which has the effect of improving heat dissipation efficiency.

[0005] The above technical objectives of the utility model are achieved through the following technical solutions: A battery pack for an electric aircraft, comprising:

[0006] The outer shell is in a hollow rectangular shape as a whole;

[0007] The battery cells are arranged side by side in the housing;

[0008] A fixing plate, which is arranged in a C shape and has an opening for the battery core to be embedded in;

[0009] The heat sink is integrally formed and vertically arranged at the opening positions on both sides of the fixing plate.

[0010] In a preferred example, the utility model can be further configured as follows: the heat sink is arranged in a wave shape.

[0011] In a preferred example, the utility model can be further configured as follows: both the upper end surface and the lower end surface of the shell are provided with plug holes for the ends of the heat sink to be plugged in.

[0012] In a preferred example, the utility model can be further configured as follows: clamping plates for clamping the two ends of the battery core are provided at both ends of the fixing plate.

[0013] In a preferred example, the present invention can be further configured as follows: both ends of the fixing plate are provided with L-shaped brackets that abut against the inner wall of the shell.

[0014] In a preferred example, the present invention may be further configured as follows: a thermal pad is provided between the outer wall of the battery core and the surface of the adjacent fixing plate.

[0015] In a preferred example, the present invention can be further configured as follows: connecting frames are provided between the fixing plates at the two ends and the inner walls at both ends of the shell.

[0016] In a preferred example, the utility model can be further configured as follows: the connecting frame includes four U-shaped connecting pieces, the four connecting pieces are divided into two layers, and the openings of the connecting pieces in the upper layer and the lower layer are arranged opposite to each other.

[0017] In summary, the utility model has the following beneficial effects:

[0018] 1. By setting up a mounting structure that integrates a fixing plate and a heat sink, the battery cell can be fixed and the heat dissipation of the battery cell can be ensured. While satisfying the requirement of fixing the battery pack, the number and weight of the structure are reduced. At the same time, the one-piece molding setting makes the heat transfer efficiency high and the heat dissipation efficiency increased;

[0019] 2. By setting up the wavy heat sink, the contact area between the heat sink and the air is increased compared with the flat heat sink, thus improving the heat dissipation effect;

[0020] 3. By setting up a thermal conductive pad, the heat generated by the battery cell can be promptly discharged to improve the heat dissipation efficiency and heat dissipation effect of the battery cell. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of an embodiment;

[0022] Figure 2 It is a schematic structural diagram of a fixing plate and a battery cell of an embodiment.

[0023] Figure numerals: 1. shell; 2. battery cell; 3. fixing plate; 4. heat sink; 5. clamping plate; 6. bracket; 7. socket; 8. thermal pad; 9. connecting frame. DETAILED DESCRIPTION

[0024] The utility model is further described in detail below in conjunction with the accompanying drawings.

[0025] like Figure 1 , Figure 2 As shown, a battery pack for an electric aircraft includes a housing 1, a battery cell 2, a fixing plate 3 and a heat sink 4.

[0026] like Figure 1 , Figure 2As shown, the housing 1 is in a hollow rectangular shape as a whole, and the battery cells 2 are arranged side by side in the housing 1. The fixing plate 3 is in a C-shape and has an opening, and allows the battery cells 2 to be embedded. Clamps 5 for clamping the battery cells 2 are provided at both ends of the fixing plate 3 to achieve stable clamping and fixing of the battery cells 2.

[0027] like Figure 1 , Figure 2 As shown, both ends of the fixing plate 3 are provided with L-shaped brackets 6 that abut against the inner wall of the shell 1 to limit the lateral sliding of the battery cell 2 and form a heat dissipation channel between the shell 1 and the battery cell 2 to ensure timely dissipation of heat from the battery cell 2, improve the heat dissipation effect, and ensure the normal operation of the battery cell 2.

[0028] like Figure 1 , Figure 2 As shown, the heat sink 4 is integrally formed and vertically arranged at the openings on both sides of the fixing plate 3. The integrally formed arrangement makes the heat transfer efficiency higher and the heat dissipation efficiency increased compared to the split arrangement. The heat sink 4 is arranged in a wave shape, and the contact area between the heat sink 4 and the air is increased compared to the flat heat sink 4, thereby improving the heat dissipation effect.

[0029] like Figure 1 , Figure 2 As shown, the upper and lower end surfaces of the housing 1 are both provided with sockets 7 for plugging the ends of the heat sink 4, so as to fix the heat sink 4 and ensure that the heat sink 4 will not bend, thereby ensuring the heat dissipation effect of the heat sink 4, and at the same time, it can also realize the upper and lower direction limit fixation of the battery cell 2 to ensure the stability of the battery cell 2.

[0030] like Figure 1 , Figure 2 As shown, a thermal pad 8 is provided between the outer wall of the battery core 2 and the surface of the adjacent fixing plate 3 to timely conduct the heat generated by the battery core 2 and improve the heat dissipation efficiency and heat dissipation effect of the battery core 2 .

[0031] like Figure 1 , Figure 2 As shown, connecting frames 9 are provided between the fixing plates 3 at the two ends and the inner walls of the housing 1 at both ends, so as to limit the longitudinal direction of all the battery cells 2 and prevent the battery cells 2 from sliding longitudinally, thereby effectively ensuring the stability of the battery cells 2 .

[0032] like Figure 1 , Figure 2 As shown, the connecting frame 9 includes four U-shaped connecting pieces, which are divided into two layers, and the openings of the upper and lower connecting pieces are arranged opposite to each other. Therefore, by arranging the U-shaped connecting pieces, the connecting pieces have a certain shock-absorbing function, so when the battery cell 2 is working or impacted, the connecting pieces can unload the force, prevent the battery cell 2 from being damaged, and ensure the service life of the battery cell 2.

[0033] The specific embodiments are merely explanations of the present invention and are not limitations of the present invention. After reading this specification, those skilled in the art may make modifications to the embodiments without any creative contribution as needed. However, as long as they are within the scope of the claims of the present invention, they are protected by the patent law.

Claims

1. A battery pack for an electric aircraft, characterized in that: include: The outer shell (1) is in the shape of a hollow rectangle as a whole; The battery cells (2) are arranged side by side in the housing (1); A fixing plate (3) is arranged in a C shape and has an opening into which the battery core (2) is embedded; The heat sink (4) is integrally formed and vertically arranged at the opening positions on both sides of the fixing plate (3).

2. A battery pack for electric aircraft according to claim 1, characterized in that: The heat sink (4) is arranged in a wave shape.

3. A battery pack for electric aircraft according to claim 2, characterized in that: The upper end surface and the lower end surface of the housing (1) are both provided with plug holes (7) for plugging the ends of the heat sink (4).

4. The battery pack for electric aircraft according to claim 1, characterized in that: Clamps (5) for clamping the two ends of the battery core (2) are provided at both ends of the fixing plate (3).

5. The battery pack for electric aircraft according to claim 4, characterized in that: Both ends of the fixing plate (3) are provided with L-shaped brackets (6) that abut against the inner wall of the outer shell (1).

6. The battery pack for electric aircraft according to claim 1, characterized in that: A heat-conducting pad (8) is provided between the outer wall of the battery core (2) and the surface of the adjacent fixing plate (3).

7. The battery pack for electric aircraft according to claim 1, characterized in that: Connecting frames (9) are provided between the fixing plates (3) at the two ends and the inner walls at both ends of the outer shell (1).

8. The battery pack for electric aircraft according to claim 7, characterized in that: The connecting frame (9) comprises four U-shaped connecting plates, which are divided into two layers, and the openings of the connecting plates in the upper layer and the lower layer are arranged opposite to each other.

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