摘要
为了给基于预测命中点法的高超声速飞行器中制导拦截提供先验知识,提出高超声速飞行器的轨迹预测方法。首先,给出高超声速环境下与目标姿态近似线性的气动参数;其次,针对气动参数作控制量的运动模型,设计自适应交互多模型(IMM)跟踪算法,并进行性能有效性验证;然后,根据气动参数特性和目标假设机动方式,设计基于最小二乘拟合的轨迹预测方法。通过对目标轨迹进行跟踪和预测仿真,预测100s的位置误差均小于5km,速度误差均小于100m/s,结果表明基于自适应IMM的轨迹预测方法对有规律机动的目标进行轨迹预测,效果良好。
To afford the prior information for intercepting the hypersonic vehicle through midcourse guidance based on pre- dicted impact point, a strategy for trajectory prediction of the hypersonic reentry-glide vehicle is proposed. A set of aerody- namic parameters, which are linearly related to the target attitude, is given. The adaptive interactive multiple model （IMM） tracking algorithm is developed based on the dynamic model with aerodynamic parameters being the control input. The ef- fectiveness of the algorithm is verified： Considering the linear characteristic of the parameters and the supposed maneuvering manners of the target, a method for trajectory prediction based on the least-square fitting is developed. Simulations show that in 100 s, the predicted position errors are less than 5 km, and the predicted velocity errors are less than 100 m/s, pro-ving the effectiveness of the strategy in predicting the trajectories of regular maneuvering targets.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2016年第11期3466-3475,共10页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(61573374
61503408)
航空科学基金(20150196006
20140196004)~~
关键词
高超声速飞行器
目标跟踪
预测
自适应
交互多模型
拟合
hypersonic vehicle
target tracking
prediction
adaptive
interactive multiple model
fitting
