Accurately tracking hypersonic gliding vehicles via an LEO mega-constellation in relay tracking mode

In order to effectively defend against the threats of the hypersonic gliding vehicles(HGVs),HGVs should be tracked as early as possible,which is beyond the capability of the ground-based radars.Being benefited by the developing megaconstellations in low-Earth orbit,this paper proposes a relay tracking mode to track HGVs to overcome the above problem.The whole tracking mission is composed of several tracking intervals with the same duration.Within each tracking interval,several appropriate satellites are dispatched to track the HGV.Satellites that are planned to take part in the tracking mission are selected by a new derived observability criterion.The tracking performances of the proposed tracking mode and the other two traditional tracking modes,including the stare and track-rate modes,are compared by simulation.The results show that the relay tracking mode can track the whole trajectory of a HGV,while the stare mode can only provide a very short tracking arc.Moreover,the relay tracking mode achieve higher tracking accuracy with fewer attitude controls than the track-rate mode.

Coupled dynamic model of state estimation for hypersonic glide vehicle

Aiming at handling complicated maneuvers or other unpredicted emergencies for hypersonic glide vehicle tracking,three coupled dynamic models of state estimation based on the priori information between guidance variables and aerodynamics are presented. Firstly, the aerodynamic acceleration acting on the target is analyzed to reveal the essence of the target’s motion.Then three coupled structures for modeling aerodynamic parameters are developed by different ideas: the spiral model with a harmonic oscillator, the bank model with trigonometric functions of the bank angle and the guide model with the changing rule of guidance variables. Meanwhile, the comparison discussion is concluded to show the novelty and advantage of these models.Finally, a performance assessment in different simulation cases is presented and detailed analysis is revealed. The results show that the proposed models perform excellent properties. Moreover, the guide model produces the best tracking performance and the bank model shows the second; however, the spiral model does not outperform the maneuvering reentry vehicle(MaRV) model markedly.

Adaptive Sampling for Near Space Hypersonic Gliding Target Tracking

For modern phased array radar systems,the adaptive control of the target revisiting time is important for efficient radar resource allocation,especially in maneuvering target tracking applications.This paper presents a novel interactive multiple model(IMM)algorithm optimized for tracking maneuvering near space hypersonic gliding vehicles(NSHGV)with a fast adaptive sam-pling control logic.The algorithm utilizes the model probabilities to dynamically adjust the revisit time corresponding to NSHGV maneuvers,thus achieving a balance between tracking accuracy and resource consumption.Simulation results on typical NSHGV targets show that the proposed algo-rithm improves tracking accuracy and resource allocation efficiency compared to other conventional multiple model algorithms.

拦截高超声速滑翔飞行器:制导进展与展望

聚焦于临近空间拦截制导关键技术,围绕中制导、中末制导交班及末制导等关键问题对临近空间拦截制导技术前景进行展望。首先对临近空间高超声速滑翔飞行器飞行特性进行仿真与分析,并给出防御系统在滑翔段拦截的优势所在;其次,围绕临近空间拦截系统面对高超声速滑翔飞行器时存在的瓶颈进行探讨,并对中制导离线弹道生成与在线弹道生成、中末制导交班及末制导等关键技术相关研究进展进行梳理与总结;最后,结合当前研究进展、面临的挑战及未来临近空间拦截需求,研究分析临近空间拦截制导技术的发展趋势,为后续防御系统的发展提供参考。

面向高超声速滑翔目标的多模型多意图融合轨迹预测

针对高超声速滑翔目标速度快、机动强导致轨迹预测精度低且窗口有限的问题,提出了一种多模型多意图融合轨迹预测方法。首先从目标的控制规律出发,构建了纵向、侧向解耦的时变预测模型集,以升力参数、阻力参数与倾侧角幅值为特征参数,通过最小二乘法与高斯假设设计纵向模型;以倾侧角符号为特征参数,针对攻击意图、规避禁飞区以及C/S型机动等典型动作设计侧向模型。然后考虑意图距离、航向角与规避禁飞区等因素设计意图代价函数,基于贝叶斯理论推导预测模型与意图的后验概率递推公式,通过多机动模式、多意图的双层次融合提高轨迹预测准确性与鲁棒性。仿真结果表明,该方法能够应对高超声速滑翔目标的复杂机动,有效提高了长时轨迹预测精度。

一种高超声速飞行器固定时间滑模控制方法

针对高超声速飞行器再入滑翔段的姿态控制问题,提出了一种存在外部扰动、模型不确定和输入饱和约束情况下的固定时间收敛终端滑模控制器。首先,针对固定时间收敛的超螺旋二阶滑模扰动观测器,给出了一个更加精确的固定收敛时间上界。随后,构造了一种改进的变指数系数快速非奇异多变量终端滑模面。进而,基于固定时间观测器和改进的滑模面,提出了一种可以使高超声速飞行器模型在受到外部扰动、模型存在不确定参数和输入饱和约束的情况下,能够实现固定时间收敛的再入滑翔段姿态控制终端滑模控制器,并证明了其在观测器收敛前后的固定时间稳定性。该方法能够在不引入额外测量的前提下,有效避免输入饱和。最后,通过数值仿真验证了所提出的控制方法的有效性。

高速飞行器编队通信保持控制与协同制导技术研究综述

在高速武器平台网络化的背景下,对于高速滑翔飞行器(以下简称“高速飞行器”)的研究不再局限于多约束下的制导方法,而是亟须破解多飞行器协同制导控制技术难题。通过总结部分军事大国研制高速飞行器的发展历程,分析了目前多飞行器协同作战的发展现状与趋势,进而引出研究多飞行器协同制导控制技术的必要性。随后分别对编队通信保持控制技术、带飞行时间约束的协同制导控制技术以及带飞行角度约束的协同制导控制技术的研究现状进行了梳理,为多高速飞行器协同作战探索解决思路,最后对多飞行器协同制导控制技术的未来发展方向进行了展望。

HGV平衡滑翔式轨迹可达区域计算方法研究

针对滑翔式高超声速飞行器(HGV)平衡滑翔轨迹可达区域的高精度快速计算问题,研究了一种基于降阶动力学模型和连续凸优化方法的可达区域计算方法;首先,根据"准平衡滑翔假设"条件,将再入飞行器三自由度动力学方程进行降阶处理,得到以速度为自变量的三阶动力学方程;然后,将可达区域计算问题描述为一系列满足再入走廊约束和初、末状态约束下的横程最大优化问题,将动力学方程进行线性化、离散化处理后,采用连续凸优化方法对该问题进行求解,得到了滑翔飞行器不同末端速度下的可达区域;最后,以CAV-H飞行器模型为例进行了仿真验证,结果表明,该方法具有较高的求解效率和可达区域计算精度。

基于滚动时域估计的高超声速飞行器轨迹跟踪

针对高超声速飞行器高精度轨迹跟踪问题,提出一种将滚动时域估计与交互式多模型算法相结合的强机动目标轨迹跟踪算法。给出了半速度系下的高超声速飞行器滑翔段运动模型及量测模型。利用滚动时域估计方法将状态估计问题转化为有约束的优化问题,并充分考虑飞行器滑翔段物理约束。在此基础上,为应对目标不同机动模式,借助交互式多模型算法思想建立模型集对其进行近似。分别在机动模式不变和机动模式突变的情况下对算法进行了验证。结果表明,新算法采用多个模型并行估计,即时调整模型概率后进行融合输出,能够有效避免目标跟踪模型失配,可显著提高对于高超声速飞行器这类强机动目标的轨迹跟踪精度。

高超声速飞行器改进阻力加速度剖面设计

针对高超声速飞行器在滑翔段标称轨迹制导过程中的阻力加速度剖面设计问题,提出了一种改进的阻力加速度剖面设计方法。为增大飞行器滑翔段航程,改善飞行状态参数,设计了以能量倒数为自变量的二次函数形式剖面,通过改变剖面中点处阻力加速度值的方式对剖面形状进行调整,以满足高超声速飞行器各项约束。仿真结果表明,与传统二次函数阻力加速度剖面进行对比,该阻力加速度剖面能够增加最大滑翔距离,并改善飞行状态参数,能支持飞行器完成禁飞区绕飞任务。

基于解析解的高超声速滑翔飞行器的机动弹道设计

为了提高高超声速滑翔飞行器机动突防能力,本文研究了飞行器典型机动弹道的设计方法。首先,推导了高精度的高度-速度解析解,作为纵向弹道设计的基础。其次,基于高程解析解和横程解析解,设计了纵向机动模式和横向机动模式,实现飞行器纵向跳跃机动和横向摆动机动,分析了这两种模式对飞行器过载的影响,为实际突防中机动模式的选择提供依据;通过合理设计横向机动模式和纵向机动模式中弹道的幅值、频率和相位,实现飞行器空间螺旋机动和空间钟摆机动。最后,通过仿真验证了本文机动弹道设计方法具有较高精度,可满足实际突防设计的需求。

Trajectory prediction in pipeline form for intercepting hypersonic gliding vehicles based on LSTM

The interception problem of Hypersonic Gliding Vehicles(HGVs)has been an important aspect of missile defense systems.In order to provide interceptors with accurate information of target trajectory,a model based on an improved Long Short-Time Memory(LSTM)network for trajectory prediction pipeline is proposed for the interception of a skip gliding hypersonic target.Firstly,for trajectory prediction required by intercepting guidance laws,the altitude,velocity and velocity direction of the target are formulated in the form of analytic functions,consisting of linear decay terms and amplitude decay sinusoidal terms.Then,the dynamic characteristics of the model parameters are analyzed,and the target trajectory prediction pipeline is proposed with the prediction error considered.Finally,an improved LSTM network is designed to estimate parameters in a dynamically-updated manner,and estimation results are used for the calculation of the final trajectory prediction pipeline.The proposed prediction algorithm provides information on the velocity vector for midcourse guidance with the effect of prediction errors on interception taken into account.Simulation is conducted and the results show the high accuracy of the algorithm in HGVs’trajectory prediction which is conducive to increasing the interception success rate.

Optimal trajectory and heat load analysis of different shape lifting reentry vehicles for medium range application

The objective of the paper is to compute the optimal burn-out conditions and control requirements that would result in maximum down-range/cross-range performance of a waverider type hypersonic boost-glide(HBG) vehicle within the medium and intermediate ranges,and compare its performance with the performances of wing-body and lifting-body vehicles vis-a-vis the g-load and the integrated heat load experienced by vehicles for the medium-sized launch vehicle under study.Trajectory optimization studies were carried out by considering the heat rate and dynamic pressure constraints.The trajectory optimization problem is modeled as a nonlinear,multiphase,constraint optimal control problem and is solved using a hp-adaptive pseudospectral method.Detail modeling aspects of mass,aerodynamics and aerothermodynamics for the launch and glide vehicles have been discussed.It was found that the optimal burn-out angles for waverider and wing-body configurations are approximately 5° and 14.8°,respectively,for maximum down-range performance under the constraint heat rate environment.The down-range and cross-range performance of HBG waverider configuration is nearly 1.3 and 2 times that of wing-body configuration respectively.The integrated heat load experienced by the HBG waverider was found to be approximately an order of magnitude higher than that of a lifting-body configuration and 5 times that of a wing-body configuration.The footprints and corresponding heat loads and control requirements for the three types of glide vehicles are discussed for the medium range launch vehicle under consideration.

基于最优控制理论的高超声速飞行器轨迹生成方法

针对新型高超声速飞行器目标的实际观测场景不足、真实飞行数据难获取等导致对反导雷达目标跟踪架构、算法难以针对性优化的问题,基于最优控制理论提出了一种高超声速飞行器全阶段轨迹生成方法.利用hp-自适应伪谱法,将轨迹生成方法对应的最优控制问题转化为非线性规划问题进行求解,并输出全阶段目标飞行运动状态数据.仿真结果表明,生成的飞行场景数据完整、仿真程度高,验证了该方法的有效性.

高超声速目标运动特性及其对预警系统的影响

在建立高超声速目标运动模型的基础上,采用定量比较的方式分析其与弹道导弹的飞行路径、飞行时间和机动能力,以利于对目标进行预警探测。分析表明,典型参数条件下高超声速滑翔飞行器大气层内相对低空飞行,飞行时间比弹道导弹慢数分钟,但横向机动范围达数千公里,使对其全程探测、搜索捕获和轨迹预测困难。分析结果可为反临预警体系建设提供技术支撑。

高超声速滑翔飞行器预测校正闭环协同末制导方法

针对能量持续衰减的高超声速滑翔飞行器末制导段时间协同问题,提出一种预测飞行时间并校正飞行剖面的协同制导方法。设计了一种带有负比例导引系数的参数化飞行剖面,在辨识气动参数后快速预测剩余飞行时间;通过数值算法修正飞行剖面参数,并输出制导指令,满足单飞行器时间约束制导要求;设计闭环协同策略,在分析飞行器时间调整能力后,各飞行器协调期望飞行时间,再自主规划飞行剖面以同时攻击目标。仿真结果表明:预测校正闭环协同制导方法可以满足时间协同末制导任务需求,落点误差小于5 m,相对时间误差小于1 s。

考虑阻力系数时变的下压段半解析时间预测方法

高超声速飞行器下压段飞行环境复杂、弹道参数变化剧烈、被动减速较快,传统解析预测采用的常值阻力系数假设不再适用。考虑攻角、马赫数影响,对阻力系数表达式进行拓展,基于解析理论对复杂弹道方程加以简化,得到以剩余射程为自变量的微分方程,通过数值积分快速求解弹道诸元,提升全弹道快速规划能力。典型弹道仿真表明,与传统常值假设相比,所提方法可将俯冲下压段的时间预报误差降低到1 s左右,同时不增加计算复杂度,实现滑翔飞行器俯冲飞行时间、速度、动压的精准、快速预报。

高超声速滑翔飞行器解析协同再入制导

为实现多高超声速滑翔飞行器的协同再入,提出一种基于剩余飞行时间和剩余飞行距离估计解析解的协同再入制导方法。基于准平衡滑翔条件推导了滑翔段剩余飞行时间和剩余飞行距离估计的解析表达式;通过攻角指令设计使飞行器快速进入并保持准平衡滑翔飞行,为时间协同提供有利条件;将纵向升阻比作为设计量,利用数值算法进行预测校正,结合航向角误差走廊得到倾侧角指令,实现了时间约束下的再入制导。基于此,设计了多飞行器协同再入策略,最终实现多飞行器绝对时间约束下的协同再入制导飞行。分别在标称条件和不确定条件下进行仿真,结果表明本研究提出方法具备一定的时间调节能力和对干扰的鲁棒性。

高超声速滑翔飞行器运动性能分析

防御方对来袭高超声速滑翔飞行器存在运动建模颗粒度过粗和难以过细等问题。在给出弹道几何模型的基础上,运用升阻比表示的滑翔段至末段运动模型定量评估分析了高超声速滑翔飞行器远程打击、末段毁伤、低空突防、快速打击、侧向绕飞突防等能力,采用4种典型高超声速滑翔飞行器对性能分析结论进行了校验。分析结果表明:高超声速滑翔飞行器大气层内高速飞行的同时会极大地延长其飞行时间,可观的横向机动距离需要牺牲较远的纵向射程。

高超声速滑翔飞行器再入轨迹优化

为提高高超声速滑翔飞行器再入轨迹优化问题求解速度和精度,提出了一种将改进的麻雀智能优化同参数化设计相结合的再入轨迹方法。首先,通过Tent混沌映射和精英反向种群方法初始化种群,利用黄金正弦策略进行种群的位置更新,并通过余弦策略减少侦察者数量,采用贪婪策略对种群的最优解进行选择和更新,在增强算法全局搜索能力的同时,不影响收敛速度。然后,将高超声速再入轨迹优化问题转化为攻角剖面和倾侧角剖面的参数化设计问题,将路径约束转化为阻力加速度再入飞行走廊,保证再入过程中始终满足路径约束,利用罚函数法处理终端约束,从而使得飞行器精确命中目标。最后,采用改进的麻雀智能优化算法对设计参数进行寻优,使得目标函数最优。仿真实验表明:本研究所提出的改进麻雀算法相较于原始麻雀算法、鲸鱼算法和粒子群算法收敛速度快,得到的高超声速滑翔飞行器再入轨迹精度有了进一步的提高;蒙特卡洛仿真实验说明,本研究所提出的高超声速滑翔飞行器再入轨迹优化算法具有一定的鲁棒性。