摘要
尾焰红外信号是导弹识别、跟踪技术发展所需的重要参数。本文在利用尾喷焰流场结构的工程经验公式获得尾焰温度、浓度和压力分布的基础上,采用宽带k分布模型计算尾喷焰的辐射信号,分析了固体火箭发动机尾喷焰红外辐射信号随飞行参数的变化规律。结果表明:在所选的红外探测器工作谱带区间内,固体火箭发动机尾喷焰积分辐射强度随着喷口处燃气温度、马赫数和喷口燃气压力与大气压力比值的增大而增大,随海拔高度的上升而减小。
The infrared signal of plume is important parameter for missile identification and tracing. After the plume temperature, the gas molar concentration and pressure fields are obtained with engineering empirical formulae, the plume radiation signatures are calculated using the wide band k-distribution model. The infrared radiation signatures of solid rocket engine plume under different fly parameters are investigated. The results showed that the integral radiation intensities of solid rocket engine plume increase with the nozzle exit temperature, Mach number and the ratio of nozzle exit pressure to atmospheric pressure, but decrease with the increase of fly altitude in the IR detector＇s working spectrum region.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2009年第7期1210-1212,共3页
Journal of Engineering Thermophysics
基金
国家自然科学基金项目(No.50636010
No.50425619)
