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Discussion on neighborhood optimal trajectory online correction algorithm and its application range

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Journal of Systems Engineering and Electronics 2023年第4期34卷 1053-1062页

作者： LI Wanli LI Jiong lei humin Graduate School Air Force Engineering UniversityXi’an 710051China Air and Missile Defense College Air Force Engineering UniversityXi’an 710051China

This paper presents a neighborhood optimal trajectory online correction algorithm considering terminal time variation,and investigates its application range.Firstly,the motion model of midcourse guidance is established,and the online trajectory correction-regenerating strategy is introduced.Secondly,based on the neighborhood optimal control theory,a neighborhood optimal trajectory online correction algorithm considering the terminal time variation is proposed by adding the consideration of terminal time variation to the traditional neighborhood optimal trajectory correction method.Thirdly,the Monte Carlo simulation method is used to analyze the application range of the algorithm,which provides a basis for the division of application domain of the online correction algorithm and the online regeneration algorithm of midcourse guidance trajectory.Finally,the simulation results show that the algorithm has high real-time performance,and the online correction trajectory can meet the requirements of terminal constraint change.The application range of the algorithm is obtained through Monte Carlo simulation.

关键词： midcourse guidance online correction neighborhood optimal control application range

Coverage-based cooperative target acquisition for hypersonic interceptions

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Science China(Technological Sciences) 2018年第10期61卷 1575-1587页

作者： ZHOU Jin lei humin Air Force Engineering University Air and Missile Defense College

This paper presents a novel coverage-based cooperative target acquisition algorithm for hypersonic interceptions. Firstly, the difficulties in the hypersonic trajectory prediction are introduced which invalidate the conventionally used predicted impact point based mid-course guidance and seeker acquisition. Secondly, in order to optimally estimate and predict the target trajectory information, the interacting multiple model(IMM) algorithm is used with the constant velocity(CV) model, the constant acceleration(CA) model and the Singer model serving as the model set. The target states are described with the probability density function(PDF) based on the IMM prediction. Thirdly, the interceptor seeker target acquisition model is established which considers the blur edge region of the field of view. The cooperative target acquisition algorithm is designed by maximizing the interceptor seekers cooperative coverage of the target high probability region(HPR). Finally, digital simulations prove the effectiveness of the proposed method and reveal that the real challenge in the hypersonic target acquisition is the poor trajectory prediction accuracy which may further result to the unsteadiness of the interceptor trajectories.

关键词：合作目标超音速拦截模型设定目标轨道概率密度目标状态数字模拟

Optimal midcourse trajectory planning considering the capture region

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Journal of Systems Engineering and Electronics 2018年第3期29卷 587-600页

作者： ZHOU Jin SHAO lei WANG Huaji ZHANG Dayuan lei humin Air and Missile Defense College Air Force Engineering UniversityXi'an 710051China Unit 95948 of the PLA Jiuquan 732750China

An optimal midcourse trajectory planning approach that considers the capture region（CR） of the terminal guidance is proposed in this article based on the Gauss pseudospectral method（GPM）. Firstly, the planar CR of the proportional navigation in terminal guidance is analyzed and innovatively introduced in the midcourse trajectory planning problems, with the collision triangle（CT） serving as the ideal terminal states parameters of the midcourse phase, and the CR area serving as the robustness against target maneuvers. Secondly, the midcourse trajectory planning problem that considers the path, terminal and control constraints is formulated and the well-developed GPM is used to generate the nominal trajectory that meets the CR demands. The interceptor will reshape the trajectory only when the former CR fails to cover the target, which has loosened the critical demand for frequent trajectory modification. Finally, the simulations of four different scenarios are carried out and the results prove the effectiveness and optimality of the proposed method.

关键词： capture region（CR） collision triangle（CT） midcourse guidance trajectory planning hypersonic interception trajectory modification

基于自适应横程走廊的再入滑翔飞行器改进预测校正算法

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系统工程与电子技术 2024年第2期46卷 692-702页

作者：贺杨超李炯邵雷周池军雷虎民空军工程大学研究生院陕西西安710051 空军工程大学防空反导学院陕西西安710051

针对再入滑翔飞行器(reentry gliding vehicle,RGV)预测校正制导算法中规避逻辑和制导逻辑相分离的问题,提出了一种基于自适应横程走廊的融合算法。首先,通过飞行器侧向运动轨迹与禁飞区的相交关系,动态引入规避逻辑;同时,提出禁飞区有... 详细信息

针对再入滑翔飞行器(reentry gliding vehicle,RGV)预测校正制导算法中规避逻辑和制导逻辑相分离的问题,提出了一种基于自适应横程走廊的融合算法。首先,通过飞行器侧向运动轨迹与禁飞区的相交关系,动态引入规避逻辑;同时,提出禁飞区有效映射横程来量化影响飞行轨迹的禁飞区区域;最后,设计自适应横程走廊,动态调整走廊边界,控制倾侧角的翻转,实现规避逻辑和侧向制导逻辑的融合。仿真结果表明,在本文方法下,飞行器可以针对不同情况的禁飞区实现有效制导,对再入扰动具有一定的鲁棒性,并与制导逻辑和规避逻辑分离设计的算法相比,在保证制导精度的同时,具备更少的倾侧角翻转次数。

关键词：预测校正算法自适应横程走廊禁飞区有效映射横程

Prescribed performance neural control to guarantee tracking quality for near space kinetic kill vehicle

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Journal of Systems Engineering and Electronics 2019年第3期30卷 573-586页

作者： ZHANG Tao LI Jiong LI Weimin WANG Huaji lei humin Air and Missile Defense College Air Force Engineering University

A prescribed performance neural controller to guarantee tracking quality is addressed for the near space kinetic kill vehicle (NSKKV) to meet the state constraints caused by side window detection. Different from the traditional prescribed performance control in which the shape of the performance function is constant, this paper exploits new performance functions which can change the shape of their function according to different symbols of initial errors and can ensure the error convergence with a small overshoot. The neural backstepping control and the minimal learning parameters (MLP) technology are employed for exploring a prescribed performance controller (PPC) that provides robust tracking attitude reference trajectories. The highlight is that the transient performance of tracking errors is satisfactory and the computational load of neural approximation is low. The pseudo rate (PSR) modulator is used to shape the continuous control command to pulse or on-off signals to meet the requirements of the thruster. Numerical simulations show that the proposed method can achieve state constraints, pseudo-linear operation and high accuracy.

关键词： prescribed performance control near space kinetic kill vehicle (NSKKV) neural approximation minimal learning parameter (MLP) pseudo rate (PSR) modulator

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导引头稳定平台离散时间预设性能控制

空军工程大学学报 2024年第2期25卷 14-20页

作者：卜祥伟王雅珺雷虎民空军工程大学防空反导学院西安710051 94860部队南京210000

针对现有离散时间预设性能控制方法对滑模趋近律依赖度高、抖振缺陷明显的难题,通过创建一种摆脱了滑模控制的设计新框架,为拦截弹导引头稳定平台提出了一种离散时间预设性能控制新方法。首先,设计一种离散时间性能函数对跟踪误差的收... 详细信息

针对现有离散时间预设性能控制方法对滑模趋近律依赖度高、抖振缺陷明显的难题,通过创建一种摆脱了滑模控制的设计新框架,为拦截弹导引头稳定平台提出了一种离散时间预设性能控制新方法。首先,设计一种离散时间性能函数对跟踪误差的收敛轨迹进行包络约束;然后,定义一种离散时间转换误差并将其用于构造一种新颖的反馈函数;设计离散时间控制律对新开发的反馈函数而不是转换误差进行镇定,不仅保证了所有跟踪误差均具有期望的预设性能,还摆脱了控制算法对滑模趋近律的依赖性,从根本上解决了控制抖振难题;最后,通过数值对比仿真验证了所提方法的有效性与优势。

关键词：预设性能控制离散时间导引头稳定平台反馈函数控制抖振

Optimal midcourse trajectory cluster generation and trajectory modification for hypersonic interceptions

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Journal of Systems Engineering and Electronics 2017年第6期28卷 1162-1173页

作者： humin lei Jin Zhou Dailiang Zhai lei Shao Dayuan Zhang Air and Missile Defense College Air Force Engineering University Xi’an 710051 China Unit 95948 of the PLA Jiuquan 732750 China

The hypersonic interception in near space is a great challenge because of the target’s unpredictable trajectory, which demands the interceptors of trajectory cluster coverage of the predicted area and optimal trajectory modification capability aiming at the consistently updating predicted impact point(PIP) in the midcourse phase. A novel midcourse optimal trajectory cluster generation and trajectory modification algorithm is proposed based on the neighboring optimal control theory. Firstly, the midcourse trajectory optimization problem is introduced; the necessary conditions for the optimal control and the transversality constraints are given.Secondly, with the description of the neighboring optimal trajectory existence theory(NOTET), the neighboring optimal control(NOC)algorithm is derived by taking the second order partial derivations with the necessary conditions and transversality conditions. The revised terminal constraints are reversely integrated to the initial time and the perturbations of the co-states are further expressed with the states deviations and terminal constraints modifications.Thirdly, the simulations of two different scenarios are carried out and the results prove the effectiveness and optimality of the proposed method.

关键词： neighboring optimal control(NOC) midcourse guidance trajectory cluster generation optimal trajectory modification

Nonlinear differential geometric guidance for maneuvering target

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Journal of Systems Engineering and Electronics 2012年第5期23卷 752-760页

作者： Jikun Ye humin lei Dongfeng Xue Jiong Li lei Shao Department of Missile Engineering Missile Institute of Air Force Engineering University Sanyuan 713800 E R. China Department of Strategies Science College of Air Force Engineering University Xi'an 710051 E R. China

Based on the idea of zeroing the line of sight rate（LOSR）,a novel nonlinear differential geometric（DG） law for intercepting the agile target is proposed.In the first part,the DG formulations are utilized to describe the relatively kinematics model of missile and target,and the nonlinear DG guidance（DGG） law is proposed based on the nonlinear control theory to eliminate the influence brought by target.Further,the missile guidance commands are derived to overcome the information loss caused by decoupling condition,the new necessary initial condition is developed to guarantee capture the agile target.Then,the designed nonlinear DGG commands are transformed from an arc-length system to the time domain.A desirable aspect of the designed guidance law is that it does not require rigorous information about target acceleration.Representative numerical results show that the designed guidance law obtain a better performance than the traditional DGG law for agile target.

关键词： guidance differential geometric nonlinear control stability maneuvering target

基于控制参数估计的再入滑翔目标智能轨迹预测算法

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系统工程与电子技术 2023年第1期45卷 221-233页

作者：李明杰周池军雷虎民邵雷骆长鑫空军工程大学防空反导学院陕西西安710051

再入滑翔目标的轨迹预测是一项困难且具有意义的技术,现有利用简单函数拟合控制参数进行轨迹预测的方法,拟合精度不高且对数据的关联性不强。针对该问题,本文结合长短期时序网络提出了基于控制参数估计的智能轨迹预测算法。首先,通过设... 详细信息

再入滑翔目标的轨迹预测是一项困难且具有意义的技术,现有利用简单函数拟合控制参数进行轨迹预测的方法,拟合精度不高且对数据的关联性不强。针对该问题,本文结合长短期时序网络提出了基于控制参数估计的智能轨迹预测算法。首先,通过设计快速轨迹生成算法,结合攻角走廊模型快速生成大量机动轨迹,构建数据集。然后,建立了包含末点修正网络、控制参数修正网络及预测网络的智能轨迹预测框架,利用数据集对关键控制参数的变化规律进行学习。最后,结合目标运动模型积分外推实现轨迹的准确预测。仿真结果表明,所设计的预测算法在不同机动模式下的预测平均误差不超过1.4 km,最大误差不超过2.5 km,能够实现轨迹的快速预测,且对大气扰动造成的模型不确定性具有一定的鲁棒性。

关键词：再入滑翔目标控制参数长短期记忆网络轨迹预测