摘要
为了对临近空间高超声速飞行器进行有效探测和预警,以X-51A为例,计算火箭助推段、超燃发动机工作段和无动力滑翔段、飞行器蒙皮、喷管和尾焰的双波段红外辐射特性。红外辐射计算的关键在于温度和有效辐射面积的确定。根据修正Lees驻点热流密度方法和辐射平衡时的辐射传热公式,计算出蒙皮的温度。用加力燃烧的涡喷发动机模型近似计算喷管的温度。把导弹尾焰温度分布场模型进行三段式简化,模拟出尾焰的红外辐射特性。仿真结果表明,在X-51A的不同飞行阶段,从不同探测角度观察到的各辐射部位对总体红外辐射贡献率差异较大;速度对蒙皮的红外辐射影响较大,而喷管和尾焰的红外辐射与火箭和超燃冲压发动机的燃烧状态有关。分析指出,当高超声速飞行器飞行姿态发生变化,或者在不同的飞行阶段,更适合采用双波段进行探测。
Quantitative analyses are performed on the infrared radiation of X-51 A’sskin, nozzle, and plume in dual bands from the boost phase to the glide phase. These analyses are essential for the effective and early-warning detection of hypersonic vehicles in near space. Temperature and effective radiation area are key parameters in infrared radiation computation. The skin temperature of X-51 A is determined using the modified Lee’s method and heat transfer formula of radiation balance. A turbojet engine with an afterburner is used for calculating the nozzle’s approximate temperature. The plume’s infrared radiation is computed by combining the plume flow field and simplified three-segment plume model. The simulations indicate that the radiation parts have a large variance in contributing to the total infrared radiation in different flight stages and from different detection angles. Speed has a significant effect on skin radiation, whereas the nozzle and plume radiations depend on the burning state of the rocket and scramjet of X-51 A. It is concluded that dual-band detection should be applied when the flight attitude changes and in different flight stages.
作者
何苹
王莹莹
樊雷
HE Ping;WANG Yingying;FAN Lei(Information Engineering Academy,Xijing University,Xi’an 710123,China;Air and Missile Defense College,Air Force Engineering University,Xi’an 710046,China;Graduate School,Air Force Engineering University,Xi’an 710046,China)
出处
《红外技术》
CSCD
北大核心
2019年第12期1175-1180,共6页
Infrared Technology
基金
中国博士后科学基金特别资助项目（2014T71008）
关键词
红外辐射
高超声速飞行器
驻点热流
蒙皮
喷管
尾焰
infrared(IR) radiation
hypersonic vehicles
stagnation point heat flux
skin
nozzle
plume
