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. According to the demand of a guided penetration missile and the large bounce angle, the general design index of the bombshell was proposed and the flight scheme was designed and optimized.The pitch angle stabilization loop was designed in the initial bouncing section, the frequency characteristic curve was given, The middle section of the flight trajectory along the program, according to the model wind tunnel blowing test data to design and optimize the trajectory, the ballistic end of the improved proportional navigation law and propose to limit the end point of the correction.Numerical simulation shows that the flight plan to meet the penetration range And the end of the target attitude target requirements.