阅读说明：本技术 一种空间飞行器用锂氟化碳电池静电防护装置及方法 (Lithium fluorocarbon battery electrostatic protection device and method for space aircraft ) 是由 乔学荣 米娟 孟宪玲 于 2019-10-12 设计创作，主要内容包括：本发明涉及一种空间飞行器用锂氟化碳电池静电防护装置及方法,属于化学电源技术领域,所述锂氟化碳电池包括多个单元盖,在每个单元盖内设置有一个电池组,所述电池组由多个蓄电池并联组成；相邻两个单元盖内的电池组之间依次串联；其特征在于,所述空间飞行器用锂氟化碳电池静电防护装置包括设置于每个单元盖内的静电泄放电阻,所述单元盖通过静电泄放电阻与电池组负极连接。本发明通过在单元盖上焊接静电泄放电阻(RJ24/0.25W),与负极柱相连接,将单元壳上的静电泄放至电池回路中,进而实现防静电的功能。(The invention relates to a lithium fluorocarbon battery electrostatic protection device and method for a space aircraft, belonging to the technical field of chemical power sources, wherein the lithium fluorocarbon battery comprises a plurality of unit covers, a battery pack is arranged in each unit cover, and the battery pack is formed by connecting a plurality of storage batteries in parallel; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the negative electrode of the battery pack through the electrostatic discharge resistors. According to the invention, the static discharge resistor (RJ24/0.25W) is welded on the cell cover and connected with the negative pole column, so that static on the cell shell is discharged into a battery loop, and the function of static prevention is further realized.)

1. A lithium fluorocarbon cell electrostatic protection device for a space aircraft comprises a plurality of unit covers, wherein a battery pack is arranged in each unit cover and consists of a plurality of storage batteries in parallel connection; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the negative electrode of the battery pack through the electrostatic discharge resistors.

2. The lithium fluorocarbon cell electrostatic protection device for space vehicles of claim 1, wherein the electrostatic discharge is solder-welded into the cell cover.

3. The electrostatic protection device for the lithium-carbon fluoride battery for the space aircraft according to claim 1 or 2, wherein the electrostatic discharge resistor consists of two resistors connected in parallel.

4. A method of manufacturing a lithium fluorocarbon cell electrostatic discharge protection device for a space vehicle according to any of claims 1 to 3, characterized by: the method comprises the following steps:

s1, before the pole is installed on the unit cover, welding an aluminum-nickel composite belt;

s2, welding a static leakage resistance assembly with a connecting terminal, and soldering a resistance on the aluminum-nickel composite strip;

s3, fixing, gluing and sealing the static leakage resistor;

and S4, mounting the connecting terminal of the static leakage resistor on the negative pole of the unit cell in a threaded manner.

Technical Field

The invention belongs to the technical field of chemical power supplies, and particularly relates to a lithium fluorocarbon battery electrostatic protection device and method for a space aircraft.

Background

The lithium fluorocarbon battery is a system with the highest specific energy in the lithium primary battery, and the 0.01C discharge specific energy of the flexible package lithium fluorocarbon battery is up to 720 Wh/kg. The small-capacity lithium fluorocarbon battery has 18650 type and D type structures, and the large-capacity lithium fluorocarbon battery adopts a flexible packaging structure. When the flexible packaging structure is applied to a space aircraft, the sealing performance of the flexible packaging structure does not meet the requirement on the leakage rate of the battery in a vacuum environment, so the flexible packaging structure and the metal shell sealing structure are required to be adopted.

In the use of the spacecraft, an isolated metal conductor is not allowed to exist in the battery pack according to the reliability design requirement, so that the damage of static accumulation to the battery is avoided.

In the unit cell, a unit shell and a cover are welded into a whole, a positive pole column and a negative pole column are installed on the unit cover, a T-shaped gasket is used for insulation, and an O-shaped ring is used for realizing a compression sealing structure of the pole column. The unit shell and the unit cover are made of aluminum alloy materials so as to reduce the weight of the structure and realize high specific energy of the battery pack. Because the single batteries are in a flexible package structure, the single batteries in the unit batteries can be connected in series and in parallel, and the single batteries are insulated from the shell. Therefore, the metal case is an isolated conductor in the unit cell structure of the flexible package + metal case.

In order to realize the electrostatic discharge of the unit shell, an electrostatic discharge loop needs to be provided, and the spacecraft requires equipotential grounding, which is in contradiction with the fact that batteries in the series-connected loop must be isolated.

Disclosure of Invention

The invention provides a lithium fluorocarbon battery electrostatic protection device and method for a space aircraft, aiming at solving the technical problems in the prior art, wherein an electrostatic discharge resistor (RJ24/0.25W) is welded on a cell cover and is connected with a negative pole column, so that the static on a cell shell is discharged into a battery loop, and the function of preventing static is further realized.

The invention provides a lithium fluorocarbon battery electrostatic protection device for a space aircraft, wherein the lithium fluorocarbon battery comprises a plurality of unit covers, a battery pack is arranged in each unit cover, and the battery pack is formed by connecting a plurality of storage batteries in parallel; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the cathode of the battery pack through the electrostatic discharge resistors.

Further, the electrostatic discharge is resistance welded in the cell cover.

Further, the static leakage resistor is formed by connecting two resistors in parallel.

The second purpose of the invention is to provide a method for manufacturing the lithium fluorocarbon cell electrostatic protection device for the space aircraft, which comprises the following steps:

s1, before the pole is installed on the unit cover, welding an aluminum-nickel composite belt;

s2, welding a static leakage resistance assembly with a connecting terminal, and soldering a resistance on the aluminum-nickel composite strip;

s3, fixing, gluing and sealing the static leakage resistor;

and S4, mounting the connecting terminal of the static leakage resistor on the negative pole of the unit cell in a threaded manner.

The invention has the advantages and positive effects that:

1) the electrostatic protection design is realized, and no isolated conductor exists in the battery pack;

2) the electrostatic discharge of the cell shell is solved in the battery, so that the complex wiring process is reduced;

3) the isolation of structure is realized through the insulation board between the cell of establishing ties, does not have the electric leakage latent route, and the insulation between the cell is destroyed under the trouble condition, and the static bleeder resistor is fused by heavy current, and the cell shell is insulated with the negative pole post, forms short-circuit protection.

Drawings

Fig. 1 is a circuit diagram of a preferred embodiment of the present invention.

Detailed Description

In order to further understand the contents, features and effects of the present invention, the following embodiments are illustrated and described in detail with reference to the accompanying drawings:

referring to fig. 1, a lithium fluorocarbon battery electrostatic protection device for a space vehicle includes a plurality of unit covers, a battery pack is disposed in each unit cover, and the battery pack is formed by connecting a plurality of storage batteries in parallel; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the cathode of the battery pack through the electrostatic discharge resistors. The two battery packs (unit cells) connected in series are structurally isolated from each other by an insulating plate.

Preferably, the electrostatic discharge is resistance welded into the cell cover.

The static leakage resistor is formed by connecting two resistors in parallel.

The working principle of the preferred embodiment is as follows:

and a metal film resistor is connected between the cell shell and the negative electrode in series, so that the cell shell and the negative electrode are at the same potential, and a discharge passage is provided for the static electricity accumulated on the cell shell.

A method for manufacturing the lithium fluorocarbon cell electrostatic protection device for the space aircraft comprises the following steps:

1) before the unit cover is provided with the pole, an aluminum-nickel composite belt is welded at a position specified by the process by using an ultrasonic welding machine;

2) welding a static leakage resistor assembly with a wiring terminal, and soldering a resistor on the aluminum-nickel composite belt;

3) fixing, gluing and sealing the resistor;

4) and mounting the wiring terminal of the static leakage resistor on the negative pole column of the unit cell in a threaded manner.

The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications, equivalent changes and modifications made to the above embodiment according to the technical spirit of the present invention are within the scope of the technical solution of the present invention.