基于部件分解法的运载火箭RCS仿真计算方法

为估算运载火箭的RCS（Radar Cross Section,雷达散射截面积）,采用部件分解法对运载火箭进行电磁散射几何建模,根据飞行过程中运载火箭和雷达的几何关系建立雷达照射目标视线角的计算模型,并运用高频散射理论提出运载火箭RCS的仿真计算方法;最后,对运载火箭的静态RCS和动态RCS进行仿真计算与分析.结果表明：对运载火箭电磁散射几何建模合理可行,提出的火箭RCS计算方法可以满足工程应用需要.采用该方法仅修改几何建模中的模型结构和部分尺寸参数即可方便计算不同型号运载火箭的RCS特性,可以为航天测控雷达系统设计和布站优化提供依据.

Launch Vehicle RCS Simulation and Computing Method Based on Component Decomposition

Component decomposition method is used to model the electromagnetic scattering geometry of spacecraft launch vehicles to estimate their RCS （Radar Cross Section）. Based on the geometric relationship between a launch vehicle and a radar during flight, a computing model is established for radar target illumination aspect angle. An RCS simulation and computing method is put forward with high frequency electromagnetic scattering theory. Static RCS and dynamic RCS of launch vehicles are simulated and analyzed, and the results show that the electromagnetic scattering geometry modeling method presented in the paper is feasible and valid and the RCS computing method meets engineering requirements. The RCS characteristics of different models of launch vehicles can be computed in a convenient manner by changing model structure and some dimensions during geometric modeling. The approach also provides basis for optimization of radar system design and station distribution for spacecraft instrumentation.