Satellite battery pack resistant to high intensity vibrations

Abstract

The utility model discloses a kind of satellite battery pack devices of high-intensity vibration resistance, including bottom plate, cover in the upper portion of bottom plate gland, multiple battery monomers are set between bottom plate and gland, support for fixing the both ends of battery monomer is fixed in the upper portion of bottom plate gland, wherein: the front side of the bottom plate is fixed with electric connector support, the upper surface of the electric connector support is mounted electric connector;The lower end surface of the bottom plate is attached with heater, the rear side of the bottom plate is fixed with grounding resistance component;The surface of the battery monomer is pasted with thermistor, and each battery monomer is electrically connected by bus bar between each battery monomer.The satellite battery pack device of high-intensity vibration resistance provided by the utility model can make structure to each battery clamping position fixed, battery pack meets high-intensity vibration requirement and has buffering effect, without damaging battery. Realize high vibration resistance intensity, small size, lightweight requirement.

Description

Technical Field

[0001] This utility model belongs to the field of satellite energy system technology, specifically, it relates to a satellite battery pack device resistant to high-intensity vibration. Background Technology

[0002] As the energy storage and power supply unit of a satellite, the reliability of the battery pack directly determines the success or failure of the entire satellite mission. During satellite launch, the battery pack needs to withstand the extreme mechanical environment generated by the launch vehicle, including continuous high-intensity random vibration and transient impact. These severe vibration and impact loads may cause damage to the internal structure of the battery pack or performance degradation, mainly manifested as: (1) failure of connection between battery cells: the wires and connecting pieces connected in series or in parallel in the battery string break or loosen due to vibration fatigue, resulting in circuit interruption. (2) damage to structural components: the brackets, pressure plates and other structural components that fix the battery modules crack or even break due to resonance or overstress, losing their fixing function. (3) relative displacement and friction between battery cells: the relative movement between loosely fixed battery cells or between the battery cells and structural components may damage the insulation layer of the battery shell and cause a short circuit due to long-term friction; at the same time, the relative displacement will cause the connecting parts to bear additional stress.

[0003] Currently, traditional satellite battery pack mounting methods mostly employ a simple "end plate + tie rod" approach or rely on the overall rigidity of the module's outer shell. While these methods are effective under static or low-level vibrations, they often fall short when facing the high-intensity, wide-bandwidth vibration environment generated by next-generation high-thrust, lightweight launch vehicles. Their designs typically suffer from limitations such as uneven stiffness and strength distribution, insufficient damping, and localized stress concentration.

[0004] To address the aforementioned issues, a novel battery pack structure is needed that can effectively solve these problems while ensuring structural strength to meet aerospace requirements, and also meeting the requirements of small size and lightweight. Utility Model Content

[0005] The purpose of this invention is to address the shortcomings and deficiencies of existing satellite battery packs, thereby providing a new type of satellite battery pack device that is resistant to high-intensity vibration. It not only has excellent vibration resistance but also a compact and lightweight structure, meeting aerospace requirements and being easy to assemble.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A satellite battery pack device resistant to high-intensity vibration includes a base plate, a cover fitted over the base plate, multiple battery cells disposed between the base plate and the cover, and brackets fixed on both sides of the cover above the base plate for fixing the ends of the battery cells, wherein:

[0008] An electrical connector bracket is fixed to the front side of the base plate, and an electrical connector is mounted on the upper surface of the electrical connector bracket; a heater is attached to the lower end face of the base plate, and a grounding resistor assembly is fixed to the rear side of the base plate.

[0009] The surface of each battery cell is covered with a thermistor, and the battery cells are electrically connected to each other through a busbar.

[0010] According to this utility model, the base plate is a square aluminum alloy integral molded part with a plurality of threaded holes on its upper surface. The cover is a square aluminum alloy integral molded part adapted to the base plate, and a corresponding number of screw through holes are opened on its two sides corresponding to the positions of the threaded holes. The two are tightly fixed by fasteners.

[0011] Furthermore, the inner surface of the base plate is provided with a plurality of arc grooves with equal center spacing. The curvature of the arc grooves is adapted to the cylindrical surface of the battery cell. A polyimide film is adhered to the surface, and thermally conductive silicone rubber is filled between the polyimide film and the battery cell to form a silicone rubber filler layer.

[0012] Preferably, two rectangular grooves are formed at both ends of the arc groove on the base plate. Silicone rubber is laid in the rectangular grooves. The end of the bracket is embedded in the rectangular groove and is tightly bonded to the silicone rubber and cured, thereby fixing it to both sides of the pressure cap above the base plate.

[0013] Preferably, the lower surface of the base plate has a concave plane, the heater is fitted and fixed on the concave plane, and the lower surface of the base plate also has a lead wire through hole for the heater lead wire to pass through and connect to the electrical connector.

[0014] Furthermore, each of the four right-angled positions of the base plate has a mounting hole, and each mounting hole contains an insulating sleeve for insulation when the device is installed with the satellite platform.

[0015] According to this utility model, the inner surface of the cover is provided with a plurality of cover arc grooves that correspond one-to-one with the arc grooves of the base plate. A polyimide film is pasted in the cover arc grooves, and silicone rubber is filled between the cover and the battery cell. After curing, it forms radial limiting and bonding fixation.

[0016] Furthermore, the outer surface of the pressure cap is provided with several weight-reducing holes. These holes serve two purposes: firstly, to reduce the overall weight of the device, and secondly, to provide lead-out channels for the thermistor wires attached to the surface of the battery cell.

[0017] According to this utility model, the bracket is provided with a plurality of equally spaced circular slots. The diameter of the circular slots is adapted to the outer diameter of the cylindrical battery cell. The two ends of the battery cell are embedded in the circular slots to achieve axial positioning and equally spaced arrangement of the battery cells.

[0018] Preferably, the center distance between the bottom plate arc groove, the circular hole groove of the bracket, and the pressure cap arc groove is the same, and all three are adapted to the size of the battery pack.

[0019] This utility model has the following beneficial effects:

[0020] This invention provides a small battery pack device resistant to high-intensity vibration. This device allows the structure to fix each battery in place, ensuring the battery pack meets the requirements for high-intensity vibration while also providing a buffering effect without damaging the batteries. It achieves high vibration resistance, small size, and lightweight design. Attached Figure Description

[0021] Figure 1 This is an overall schematic diagram of the satellite battery pack device that resists high-intensity vibration according to this utility model.

[0022] Figure 2 for Figure 1 Top view.

[0023] Figure 3 This is a schematic diagram of the front (upper surface) view of the base plate of this utility model.

[0024] Figure 4 This is a schematic diagram of the reverse side (lower surface) of the base plate of this utility model.

[0025] Figure 5 This is a schematic diagram of the structure of the pressure cap of this utility model.

[0026] Figure 6 This is a schematic diagram of the structure of the bracket of this utility model.

[0027] Drawing number explanation:

[0028] 1-Base plate; 2-Cover; 3-Battery cell; 4-Bracket; 5-Electrical connector bracket; 6-Electrical connector; 7-Thermistor; 8-Grounding resistor assembly; 9-Busbar; 11-Base plate arc groove; 12-Rectangular groove; 13-Concave plane; 14-Threaded hole; 15-Mounting hole; 16-Insulating sleeve; 17-Lead wire through hole; 21-Cover arc groove; 22-Weight reduction hole; 23-Screw through hole; 41-Circular slot; 81-Grounding screw; 82-Grounding resistor Detailed Implementation

[0029] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the following embodiments are for illustrative purposes only and are not intended to limit the scope of the present invention.

[0030] Unless otherwise specified, the fixing methods described in the following embodiments are all known in the prior art, such as opening screw holes and fixing with screws.

[0031] like Figure 1 and Figure 2 As shown, this utility model is a satellite battery pack device resistant to high-intensity vibration, including a base plate 1, a pressure cover 2 covering the top of the base plate 1, multiple battery cells 3 disposed between the two, and brackets 4 fixed on both sides of the pressure cover 2 on the top of the base plate 1 for fixing the ends of the battery cells 3. It also includes an electrical connector bracket 5 fixed to the front side of the base plate 1, an electrical connector 6 mounted on the upper surface of the electrical connector bracket 5, a heater (not shown) attached to the lower end face of the base plate 1, a thermistor 7 attached to the surface of the battery cells 3, and a grounding resistor assembly 8 fixed to the rear side of the base plate 1. The battery cells 3 are electrically connected to each other through busbars 9, which are spot-welded to the electrodes of the battery cells 3. All components are structurally adapted and fixedly connected to form an integrated vibration-resistant structure.

[0032] Combination Figure 3 and Figure 4As shown, the base plate 1 is a square, one-piece aluminum alloy component, serving as the basic support and heat-conducting part of the device. Its inner surface has several equally spaced arc grooves 11, the curvature of which perfectly matches the cylindrical surface of the battery cell 3, for radial positioning of the battery cell 3. In this embodiment, there are seven arc grooves 11. A polyimide film is adhered to the surface of each arc groove 11, and a silicone rubber filler layer formed by GD480 thermally conductive silicone rubber is filled between the polyimide film and the battery cell 3. After curing, this achieves bonding and fixation between the battery cell 3 and the base plate 1, as well as heat conduction. Two rectangular grooves 12 are formed at both ends of the arc grooves 11 on the base plate 1. GD414 silicone rubber is laid inside the rectangular grooves 12 for bonding and fixing the ends of the bracket 4. It is easy to understand that the type of silicone rubber is not limited to the specific GD480 or GD414 types in this embodiment and can be adjusted according to actual needs. The lower surface of the base plate 1 has a concave plane 13 for fitting and fixing the heater so that heat can be conducted to the battery cell 3 through the base plate 1; the upper surface of the base plate 1 has a plurality of threaded holes 14, including: three on each of the left and right sides for fixing to the cover 2 with screws; two on the front side for fixing the electrical connector bracket 5; and one on the rear side for installing the grounding resistor assembly 8; it is easy to understand that the number of threaded holes 14 is not limited to the specific number in this embodiment and can be adjusted according to actual needs. The grounding resistor assembly 8 includes a grounding screw 81, a grounding resistor 82 and a flat washer (not shown in the figure); the base plate 1 has one mounting hole 15 at each of the four right-angle positions, and an insulating sleeve 16 is nested in each mounting hole 15 (see Figure 1 This is used to achieve insulated installation when mounting the entire device to the satellite platform. The lower surface of the base plate 1 also has a lead wire through-hole 17 for the heater's lead wire to pass through and connect to the electrical connector 6.

[0033] like Figure 5As shown, the pressure cap 2 is a square aluminum alloy integral molded part adapted to the base plate 1. Its outer surface is a flat plane, and its inner surface has several pressure cap arc grooves 21 that correspond one-to-one with the base plate arc grooves 11 of the base plate 1, which are used to radially position the battery cell 3 from above. Polyimide film is also pasted inside the pressure cap arc grooves 21, and GD414 silicone rubber is filled between the pressure cap and the battery cell 3. After curing, it forms radial limiting and adhesive fixation. Several weight reduction holes 22 are opened on the outer surface of the pressure cap 2. The weight reduction holes 22 reduce the overall weight and also provide lead-out channels for the thermistor 7 pasted on the battery surface, which is convenient for real-time monitoring of battery temperature. The two sides of the pressure cap 2 have a corresponding number of screw through holes 23 corresponding to the threaded holes 14 of the base plate 1. During assembly, the fasteners pass through the screw through holes 23 in sequence and are screwed into the threaded holes 14 of the base plate 1, thereby tightly fixing the pressure cap 2 to the base plate 1.

[0034] like Figure 6 As shown, bracket 4 is a one-piece molded part made of PC material, and is plate-shaped in shape. It has two ( Figure 5 One of them is shown), corresponding to the two ends of the battery cell 3. The bracket 4 has several equally spaced circular slots 41, the same number as the arc grooves 11 on the base plate; the diameter of the circular slots 41 is adapted to the outer diameter of the cylindrical battery cell 3, and the two ends of the battery cell 3 are embedded in the circular slots 41, achieving axial positioning and equally spaced arrangement of the battery cell 3, facilitating the subsequent spot welding process of the electrodes of the battery cell 3 to the busbar 9. The end of the bracket 4 is embedded in the rectangular groove 12 of the base plate 1, tightly adhering to the GD414 silicone rubber inside the groove, forming a strong bond after curing.

[0035] The assembly relationship of this utility model is as follows: First, the seven battery cells 3 are arranged in a single row array, with their two ends respectively embedded in the circular slots 41 of the two brackets 4 for axial positioning, thus obtaining a battery-bracket assembly. Then, this battery-bracket assembly is placed on the base plate 1, ensuring that the cylindrical surface of each battery cell 3 falls into the corresponding arc groove 11 of the base plate, and is bonded and fixed using a silicone rubber filling layer. Finally, the pressure cap 2 is closed, so that its arc groove 21 precisely locks the upper part of the battery cell 3, and screws are screwed through the screw holes 23 of the pressure cap 2 into the threaded holes 14 of the base plate 1 to complete the overall locking and fixing.

[0036] It should be noted that the center distances of the arc groove 11 of the base plate 1, the circular hole groove 41 of the bracket 4, and the arc groove 21 of the pressure cover 2 are completely consistent, and all three are precisely matched to the size of the battery cell 3, ensuring the effectiveness of the limiting. The aluminum alloy material used for the base plate 1 and the pressure cover 2 ensures structural strength and thermal conductivity, while the insulating plastic material of the bracket 4 and the application of polyimide film and insulating sleeve ensure the insulation safety of critical parts.

[0037] From the overall structure, each battery cell 3 is precisely positioned and fixed in three dimensions by the bottom plate arc groove 11 of the base plate 1, the circular hole groove 41 of the bracket 4, and the pressure cover arc groove 21 of the pressure cover 2. Combined with the bonding and buffering effect of the filled silicone rubber, the entire battery pack achieves integrated resistance to high-intensity vibration and vibration reduction, while also meeting the requirements of small size and lightweight.

[0038] Although the present invention has been described in detail above through specific embodiments, it should be understood that the above description is only a preferred embodiment of the present invention. Those skilled in the art can make appropriate modifications, equivalent substitutions and improvements within the spirit and principles of the present invention, all of which should be included within the protection scope of the present invention.

Claims

1. A satellite battery pack device resistant to high-intensity vibration, characterized in that, Includes a base plate (1), a pressure cap (2) covering the top of the base plate (1), multiple battery cells (3) disposed between the base plate (1) and the pressure cap (2), and brackets (4) fixed on both sides of the pressure cap (2) above the base plate (1) for fixing the ends of the battery cells (3), wherein: An electrical connector bracket (5) is fixed to the front side of the base plate (1), and an electrical connector (6) is installed on the upper surface of the electrical connector bracket (5); a heater is attached to the lower end face of the base plate (1), and a grounding resistor assembly (8) is fixed to the rear side of the base plate (1). The surface of each battery cell (3) is covered with a thermistor (7), and each battery cell (3) is electrically connected to the others through a busbar (9).

2. The satellite battery pack device resistant to high-intensity vibration according to claim 1, characterized in that, The base plate (1) is a square aluminum alloy integral molded part with several threaded holes (14) on its upper surface. The cover (2) is a square aluminum alloy integral molded part adapted to the base plate (1). The two sides of the cover are provided with a corresponding number of screw through holes (23) at the positions of the threaded holes (14). The two are tightly fixed by fasteners.

3. The satellite battery pack device resistant to high-intensity vibration according to claim 1, characterized in that, The inner surface of the base plate (1) is provided with a number of base plate arc grooves (11) with equal center spacing. The curvature of the base plate arc grooves (11) is adapted to the cylindrical surface of the battery cell (3). A layer of polyimide film is pasted on the surface, and thermally conductive silicone rubber is filled between the polyimide film and the battery cell (3) to form a silicone rubber filling layer.

4. The satellite battery pack device resistant to high-intensity vibration according to claim 3, characterized in that, The bottom plate (1) has two rectangular grooves (12) at both ends of the bottom plate arc groove (11). The rectangular grooves (12) are covered with silicone rubber. The end of the bracket (4) is embedded in the rectangular groove (12) and is tightly bonded and cured to the silicone rubber, thereby fixing it to both sides of the pressure cap (2) above the bottom plate (1).

5. The satellite battery pack device resistant to high-intensity vibration according to claim 1, characterized in that, The bottom plate (1) has a concave plane (13) on its lower surface. The heater is attached and fixed to the concave plane (13). The bottom plate (1) also has a lead wire through hole (17) for the heater's lead wire to pass through and connect to the electrical connector (6).

6. The satellite battery pack device resistant to high-intensity vibration according to claim 1, characterized in that, The base plate (1) has one mounting hole (15) at each of the four right-angle positions. Each mounting hole (15) contains an insulating sleeve (16) for insulation when the device is installed with the satellite platform.

7. The satellite battery pack device resistant to high-intensity vibration according to claim 3, characterized in that, The inner surface of the cover (2) is provided with a number of cover arc grooves (21) that correspond one-to-one with the bottom arc grooves (11) of the base plate (1). A polyimide film is pasted in the cover arc grooves (21), and silicone rubber is filled between the cover and the battery cell (3). After curing, it forms radial limiting and bonding fixation.

8. The satellite battery pack device resistant to high-intensity vibration according to claim 1, characterized in that, The outer surface of the pressure cap (2) is provided with several weight-reducing holes (22). The weight-reducing holes (22) are used to reduce the overall weight of the device on the one hand, and to provide lead-out channels for the thermistor (7) attached to the surface of the battery cell (3) on the other hand.

9. The satellite battery pack device resistant to high-intensity vibration according to claim 7, characterized in that, The bracket (4) has several equally spaced circular slots (41). The diameter of the circular slots (41) is adapted to the outer diameter of the cylindrical battery cell (3). The two ends of the battery cell (3) are embedded in the circular slots (41) to achieve axial positioning and equally spaced arrangement of the battery cell (3).

10. The satellite battery pack device resistant to high-intensity vibration according to claim 9, characterized in that, The center distance between the bottom plate arc groove (11) of the bottom plate (1), the circular hole groove (41) of the bracket (4) and the pressure cover arc groove (21) of the pressure cover (2) is consistent and all are adapted to the size of the battery cell (3).

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