摘要
针对传统的侧向制导方法在气动参数存在不确定性时,因气动力和倾侧角剖面的变化而造成较大的制导误差,提出了一种基于动态航向角误差走廊的侧向制导方法.根据参考航向角误差走廊和实际升阻比的估计值在线调整航向角误差门限.在飞行轨迹末端根据当前速度和航向角误差的导数对反转点进行预测.该制导方法对气动参数摄动具有较强的鲁棒性,并避免了不必要的反转.仿真结果表明了该方法的有效性.
To improve the lateral guidance performance, a new lateral guidance approach based on the dynamic heading error corridor is proposed. The bank reversal is determined by the dynamic heading error threshold which is on-line adjusted according to the reference heading error corridor and the estimated actual lift-to-drag ratio. Near the end of the trajectory, the bank reversal is determined by the terminal heading error predictor which demands the derivative of heading error respect to the velocity and current velocity. The proposed method effectively improves the terminal guidance precision in the presence of aerodynamic model uncertainty, and prevents unnecessary bank reversals. Simulation results validate the effectiveness of the method.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2011年第1期31-35,共5页
Journal of Harbin Institute of Technology
关键词
再入
侧向制导
气动参数不确定性
动态航向角误差走廊
预测制导
re-entry
lateral guidance
aerodynamic uncertainty
dynamic heading error corridor
prediction guidance
