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针对红外系统实时跟踪捕获高速飞行弹箭目标的关键问题,提出了一种用于求解其全弹道动态红外辐射(IR)特性的方法.以典型155mm口径无控弹箭为研究对象,基于Simulink建立了模块化的6自由度(DOF)刚体弹道仿真模型,数值计算并分析了弹道诸元的变化规律.应用热网络法建立了弹体表面耦合换热动态热辐射场的物理模型,推导了弹箭高速旋转飞行的气动加热计算模型,并利用蒙特卡洛(M-C)法考虑了环境热辐射的影响.运用Runge-Kutta法耦合求解节点热平衡方程组,得到了动态气动表面传热系数、温度场以及红外辐射场的分布规律,对比分析了目标在整个飞行过程、不同部位、不同波段内的红外辐射特征.结果表明:目标发射后,其表面温度迅速升高,越靠近弹头部,温度升高速率越快,峰值温度越高;在飞行前20s内,其红外辐射特征明显;随着飞行速度衰减,热量散失较快,辐射强度较弱,且主要集中于8~14μm波段.
Aiming at the key issue that the infrared system real-time tracking and catching the target of high-speed flight missile, a method for solving the dynamic infrared radiation (IR) characteristic of its full trajectory is proposed.A typical 155mm caliber missile is taken as the research object and established based on Simulink A 6-DOF (DOF) rigid-body trajectory simulation model was built, and the variation regularities of trajectory elements were numerically calculated and analyzed.The physical model of dynamic heat radiation field coupled heat transfer was established by using thermal network method, The calculation model of aerodynamic heating for high-speed rotating flight was put forward and Monte Carlo (MC) method was adopted to consider the influence of ambient thermal radiation. The Runge-Kutta method was used to solve the thermal equilibrium equations of nodes, and the dynamic aerodynamic surface heat transfer coefficient, temperature field And the distribution of infrared radiation field, the infrared radiation characteristics of the target in the whole flight process, different parts and different wavebands were contrastively analyzed.The results show that the surface temperature of the target rises rapidly after the target launches, and the closer to the warhead, the higher the temperature The faster the rate, the higher the peak temperature. Within 20 seconds before flight, the infrared radiation characteristics are obvious. With the decay of flight speed, the heat dissipation rapidly and the radiation intensity is strong Weak, and mainly in 8 ~ 14μm band.