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impact point prediction guidance of ballistic missile in high maneuver penetration condition

Defence Technology（防务技术） 2023年第8期26卷 213-230页

作者： Yong Xian Le-liang Ren Ya-jie Xu Shao-peng Li Wei Wu Da-qiao Zhang Xi'an Research Institute of High Technology Xi'an710025China Department of Automation Tsinghua UniversityBeijing100084China

An impact point prediction(IPP) guidance based on supervised learning is proposed to address the problem of precise guidance for the ballistic missile in high maneuver penetration condition.An accurate ballistic trajectory model is applied to generate training samples,and ablation experiments are conducted to determine the mapping relationship between the flight state and the impact point.At the same time,the impact point coordinates are decoupled to improve the prediction accuracy,and the sigmoid activation function is improved to ameliorate the prediction efficiency.Therefore,an IPP neural network model,which solves the contradiction between the accuracy and the speed of the IPP,is established.In view of the performance deviation of the divert control system,the mapping relationship between the guidance parameters and the impact deviation is analysed based on the variational principle.In addition,a fast iterative model of guidance parameters is designed for reference to the Newton iteration method,which solves the nonlinear strong coupling problem of the guidance parameter solution.Monte Carlo simulation results show that the prediction accuracy of the impact point is high,with a 3 σ prediction error of 4.5 m,and the guidance method is robust,with a 3 σ error of 7.5 m.On the STM32F407 singlechip microcomputer,a single IPP takes about 2.374 ms,and a single guidance solution takes about9.936 ms,which has a good real-time performance and a certain engineering application value.

关键词： Ballistic missile High maneuver penetration impact point prediction Supervised learning Online guidance Activation function

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impact point prediction and Lateral Correction Analysis of Two-dimensional Trajectory Correction Projectiles

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Defence Technology（防务技术） 2013年第1期9卷 64-69页

作者： WANG Zhongyuan CHANG Sijiang School of Energy and Power Engineering Nanjing University of Science and Technology

Compared with the one-dimensional trajectory correction technology which adjusts longitudinal range, not only does the two-dimensional trajectory correction technology adjust the force in velocity direction, but also need to modulate the lateral force or trajectory (perpendicular to the vertical plane of fire direction). Therefore, the structure of control cabin of two-dimensional trajectory correction projectile (TDTCP) is more complicated than that of one-dimensional trajectory correction projectile (ODTCP). To simplify the structure of control cabin of TDTCP and reduce the cost, a scheme of adding a damping disk to the control cabin of ODTCP has been developed recently. The damping disk is unfolded at the right moment during its flight to change the ballistic drift of spin stabilized projectile. For this technical scheme of TDTCP, a fast and accurate impact point prediction method based on extended Kalman filter is presented. An approximate formula for predicting the ballistic drift and trajectory correction quantity is deduced. And the lateral correction capability for different fire angles and its influencing factors are analyzed. All the work is valuable for further research.

关键词： control and navigation technology of aerocraft trajectory correction damping disk trajectory ballistic drift impact point prediction

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维普期刊数据库

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Numerical Simulation and Experiment for impact point prediction of Parachute-Warhead System

Numerical Simulation and Experiment for Impact Point Predict...

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第三十九届中国控制会议

作者： Hong Zhu Qinglin Sun Jinyang Han Zengqiang Chen College of Artificial Intelligence Nankai University Department of Experiment Aerospace Life-Support Equipment Co.Ltd

Accurate modeling is crucial to the impact point prediction of a Parachute-Warhead System（PWS）.Due to the flexibility of canopies,the computation of parachute aerodynamics is a key issue in dynamic modeling.Different from the rigid aircraft,there is a strong interaction between the parachute and its surrounding fluid.Base on the Fluid-Structure Interaction（FSI）method,inflation behavior of a Disk-Gap-Band parachute is investigated firstly.In this way,the lift and drag coefficients are generated.Then,the dynamic model in the terminal falling of a PWS is established based on the obtained aerodynamic parameters.The impact point prediction is accomplished by analyzing the dynamic characteristics.Besides,a numerical simulation airdrop platform is developed accordingly.Finally,the proposed method is verified by airdrop-testing.To conclude,the results show that the modeling methods in inflation and terminal descent are effective to forecast the landing area of the PWS,which will be useful for airdrop missions.

关键词： Parachute-warhead system inflating process impact point prediction multibody dynamics

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