空空导弹中制导系统蒙特卡罗仿真研究

Monte Carlo Simulatian of Midcourse Guidance System for Medium-Range Air-to-Air Missiles

基于蒙特卡罗仿真技术 ,研究了导弹中制导方案的可行性 ,分析输入参数误差 ,初始不对准误差 ,惯性器件误差 ,目标机动 ,计算延迟等因素对导引头截获目标的影响。仿真结果表明 ,采用比例导引律和低精度的捷联惯导系统可保证中制导段结束时导引头可靠截获目标。

Our aim was to study the feasibility of using a midcourse guidance system, which was contructed from proportional guidance law and inexpensive SINS (strapdown inertial navigation system), to ensure the acquisition capability of medium range air-to-air missilie. Section 1 reviews very briefly the essentials of midcourse guidance. Section 2 describes in some detail our simulation scheme for exploring the above-mentioned feasibllity. Subsection 2.7 analyzes the effect on acquisition of initial misalignment (subsubsection 2.7.1), initial sensor errors (subsubsection 2.7.2), target position and velocity errors (subsubsection 2.7.3), target maneuvering uncertainty (subsubsection 2.7.4), seeker drift error (subsubsection 2.7.5), time delay error (subsubsection 2.7.6), and altitude error (subsubsection 2.7.7 ). The Monte Carlo simulation results, given in Table 3, show preliminarily that target acquisition can be guaranteed.