空间冷屏表面温度分布实验研究

Experimental study on surface temperature distribution of space cryogenic shield

空间冷屏是一种包裹在高速飞行器外的相变制冷装置,旨在提高近地高速飞行器的突防能力,防止其在近地轨道飞行时被红外探测器发现和拦截。为了实现弹道导弹在飞行中段的红外隐身效果,采用深冷介质相变制冷技术,建立了空间冷屏样机。实验研究了冷屏表面温度分布及质量变化,并提出了定量分析的经验模型。结果表明:该空间冷屏样机可使弹道导弹表面温度在飞行中段低于100 K,30 min内使表面红外辐射强度低于0.15 W/m2,从而满足低温红外辐射特性要求。

The space cryogenic shield is a device of phase-change refrigeration used to wrap the high- speed spacecraft up, which aims at improving penetration of near-earth high-speed spacecraft, and preventing being discovered and intercepted by infrared detector in near-earth orbit. In order to realize the effect of infrared stealth of ballistic missiles in the midcourse flight, a prototype of cryogenic shield was developed by adopting the phase-changed refrigeration of the cryogenic refrigerant. An experimental study on the surface temperature distribution and weight change of the prototype was carried out, and an empirical model was presented to make quantitative analysis. The result indicates that the prototype of space cryogenic shield may lower the surface temperature of ballistic missiles to less than 100 K, and reduce the infrared radiation of the surface to 0.15 W/m2 in 30 minutes. This cryogenic shield can meet the requirements of cryogenic infrared radiation in the space.