Temperature control device of storage battery for spacecraft

A technology for space vehicles and temperature control devices, which is applied in battery temperature control, secondary batteries, circuits, etc., can solve the problems of poor heat dissipation capacity and low flexibility of temperature control devices, and achieve high reliability, flexible device design, and guaranteed Effects of isothermalization requirements

Inactive Publication Date: 2012-07-11
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0008] In order to solve the shortcomings of the temperature control device in the prior art, such as poor heat dissipation and low flexibility, the ob

Method used

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  • Temperature control device of storage battery for spacecraft
  • Temperature control device of storage battery for spacecraft
  • Temperature control device of storage battery for spacecraft

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Example Embodiment

[0019] The preferred embodiments of the present invention will be described below in conjunction with the drawings.

[0020] figure 1 It is a schematic diagram of the structure of the temperature control device for the space vehicle battery of the present invention, figure 2 for figure 1 Side view of; such as figure 1 with figure 2 As shown in the embodiment, the device includes: the battery structural block 1 is directly installed inside the temperature control plate 2; the outer circumference of the battery structural block 1 and the inner side of the temperature control plate 2 are covered with a multilayer heat insulation component 8; The outer surface of the component 8 is coated with a high-emissivity matting black film; the inner surface of the temperature control plate 2 and the side close to the battery mounting surface are embedded with a transverse heat pipe 5; the inner surface of the temperature control plate 2 and the vicinity of the battery mounting surface A long...

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Abstract

The invention discloses a temperature control device of a storage battery for a spacecraft. The temperature control device provided by the invention comprises a temperature control plate [2]. Storage battery structure blocks [1] are installed at an inner side of the temperature control plate [2]. Transverse heating pipes are pre-embedded in a side which belongs to the temperature control plate [2] and is close to a storage battery installation surface. Vertical heating pipes [6] are pre-embedded in parts close to the storage battery installation surface. A hot expanding plate [3] is arranged at a part close to the storage battery installation surface. The hot expanding plate [3] transversely extends out of a heat dissipation plate [4]. Sides of the storage battery structure blocks [1] are provided with heating devices. The temperature control device provided by the invention solves the problem of temperature control of a high-calorific value storage battery used for a spacecraft, and has good temperature control effects, high reliability and a flexible design.

Description

technical field [0001] The invention relates to a temperature control device for a storage battery with high calorific value used in a space vehicle. Background technique [0002] As an important part of the aircraft power system, the space battery is the only power supply equipment during the phases of the aircraft entering orbit and operating in the shadow period. Batteries are sensitive to temperature. Too high or too low temperature will affect the performance and life of the battery: if the temperature is too low, the effective charge capacity of the battery cannot be guaranteed; if the temperature is too high, the charging efficiency will decrease, and the heat consumption of the battery will decrease can cause thermal runaway. Therefore, battery thermal control is crucial to the reliability of the battery and even the aircraft. [0003] The battery generates a lot of heat, which is generally more than 15% of the output power of the aircraft. Taking the current mains...

Claims

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Application Information

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IPC IPC(8): H01M10/50H01M10/617H01M10/62H01M10/653H01M10/6551H01M10/6552H01M10/6554
CPCY02E60/12Y02E60/10
Inventor 姚正平于迎军童铁峰毛云杰
Owner SHANGHAI SATELLITE ENG INST
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