某制导侵彻航弹飞行弹道研究  

Research on Trajectory of Guided Penetrating Bomb

作　　者：田亚军[1] 周刚[1] 王洪强[1] 胡军照[1] 

机构地区：[1]西北核技术研究所,西安710024

出　　处：《战术导弹技术》2011年第5期50-53,共4页Tactical Missile Technology

摘　　要：根据某制导侵彻航弹射程远、弹着角大的要求,提出该航弹的总设计指标,设计和优化了飞行方案.初始投弹段设计了俯仰角稳定回路,给出了频率特性曲线,中间段沿方案弹道飞行,根据模型风洞吹风试验数据设计和优化弹道,弹道末段采用改进型比例导引律并提出修正限制终点落角.数值仿真表明该飞行方案满足侵彻航弹对射程和末段着靶姿态的指标要求.The design indexes of the bomb are presented based on the guided penetrating bomb＇s wide range and large terminal angle＇s request,the flight scheme is introduced and optimized.At the initial bomb-dropping stage the stabilized loop of the pitching angle is designed and the frequency characteristic curve is presented.In midcourse flight the scheme trajectory is tracked by the bomb.Ballistic trajectory is designed and optimized based on the aerodynamics parameters from model bomb＇s wind tunnel test.At the end of trajectory a proportional guidance law is adopted to limit the terminal angle.Numerical simulation show the guided penetrating bomb＇s range and terminal angle satisfied.

关 键 词：侵彻航弹 方案弹道 比例导引 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程]