本文關(guān)鍵詞：基于自適應IMM的高超聲速飛行器軌跡預測　出處：《航空學報》2016年11期 　論文類型：期刊論文

  更多相關(guān)文章： 高超聲速飛行器 目標跟蹤 預測 自適應 交互多模型 擬合

【摘要】：為了給基于預測命中點法的高超聲速飛行器中制導攔截提供先驗知識,提出高超聲速飛行器的軌跡預測方法。首先,給出高超聲速環(huán)境下與目標姿態(tài)近似線性的氣動參數(shù);其次,針對氣動參數(shù)作控制量的運動模型,設(shè)計自適應交互多模型(IMM)跟蹤算法,并進行性能有效性驗證;然后,根據(jù)氣動參數(shù)特性和目標假設(shè)機動方式,設(shè)計基于最小二乘擬合的軌跡預測方法。通過對目標軌跡進行跟蹤和預測仿真,預測100s的位置誤差均小于5km,速度誤差均小于100m/s,結(jié)果表明基于自適應IMM的軌跡預測方法對有規(guī)律機動的目標進行軌跡預測,效果良好。
[Abstract]:In order to provide a prior knowledge for the guided interception of hypersonic vehicle based on predictive hit point method, a trajectory prediction method for hypersonic vehicle is proposed. The aerodynamic parameters which are approximately linear to the target attitude in hypersonic environment are given. Secondly, an adaptive interactive multi-model (IMM) tracking algorithm is designed for the motion model in which aerodynamic parameters are controlled, and the effectiveness of the algorithm is verified. Then, according to the aerodynamic parameters and the maneuvering mode of the target hypothesis, a trajectory prediction method based on least square fitting is designed, and the tracking and prediction simulation of the target trajectory is carried out. The position error and velocity error are less than 5 km and 100 m / s respectively. The results show that the trajectory prediction method based on adaptive IMM is used to predict the trajectory of the target with regular maneuvering. The effect is good.
【作者單位】： 空軍工程大學防空反導學院;
【分類號】：V249.1
【正文快照】： 網(wǎng)絡(luò)出版地址:www.cnki.net/kcms/detail/11.1929.V.20160303.1635.002.html引用格式:翟岱亮,雷虎民,李炯,等.基于自適應IMM的高超聲速飛行器軌跡預測[J].航空學報,2016,37(11):3466-3475.ZHAI DL,LEI H M,LI J,et al.Trajectory prediction of hypersonic vehicle based on a

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