Flight control for a flexible air-breathing hypersonic vehicle based on quasi-continuous high-order sliding mode

The focus of this paper is on control design and simulation for the longitudinal model of a flexible air-breathing hypersonic vehicle（FAHV）.The model of interest includes flexibility effects and intricate couplings between the engine dynamics and flight dynamics.To overcome the analytical intractability of this model,a nominal control-oriented model is constructed for the purpose of feedback control design in the first place.Secondly,the multi-input multi-output（MIMO） quasi-continuous high-order sliding mode（HOSM） controller is proposed to track step changes in velocity and altitude,which is based on full state feedback.The simulation results are presented to verify the effectiveness of the proposed control strategy.

Reference tracking control for flexible air-breathing hypersonic vehicle with actuator delay and uncertainty

This paper considers the problem of reference tracking control for the flexible air-breathing hypersonic flight vehicle with actuator delay and uncertainty.By constructing the Lyapunov functional including the lower and upper bounds of the time-varying delay,the non-fragile controller is designed such that the resulting closed-loop system is asymptotically stable and satisfies a prescribed performance cost index.The simulation results are given to show the effectiveness of the proposed control method,which is validated by excellent output reference altitude and velocity tracking performance.

Back-Stepping Control for Flexible Air-Breathing Hypersonic Vehicles Based on Uncertainty and Disturbance Estimator

A theoretical framework of nonlinear flight control for a flexible air-breathing hypersonic vehicle(FAHV)is proposed in this paper.In order to suppress the system uncertainty and external disturbance,an uncertainty and disturbance estimator(UDE)based back-stepping control strategy is designed for a dynamic state-feedback controller to provide stable velocity and altitude tracking.Firstly,the longitudinal dynamics of FAHV is simplified into a closure loop form with lumped uncertainty and disturbance.Then the UDE is applied to estimate the lumped uncertainty and disturbance for the purpose of control input compensation.While a nonlinear tracking differentiator is introduced to solve the problem of“explosion of term”in the back-stepping control.The stability of the UDE-based control strategy is proved by using Lyapunov stability theorem.Finally,simulation results are presented to demonstrate the capacity of the proposed control strategy.

HOSVD-based LPV modeling and mixed robust H_2/H_∞ control design for air-breathing hypersonic vehicle

This paper focuses on synthesizing a mixed robust H_2/H_∞ linear parameter varying（LPV） controller for the longitudinal motion of an air-breathing hypersonic vehicle via a high order singular value decomposition（HOSVD） approach.The design of hypersonic flight control systems is highly challenging due to the enormous complexity of the vehicle dynamics and the presence of significant uncertainties.Motivated by recent results on both LPV control and tensor-product（TP） model transformation approach,the velocity and altitude tracking control problems for the air-breathing hypersonic vehicle is reduced to that of a state feedback stabilizing controller design for a polytopic LPV system with guaranteed performances.The controller implementation is converted into a convex optimization problem with parameterdependent linear matrix inequalities（LMIs） constraints,which is intuitively tractable using LMI control toolbox.Finally,numerical simulation results demonstrate the effectiveness of the proposed approach.

Robust adaptive control of hypersonic vehicle considering inlet unstart

In this paper,a model reference adaptive control(MRAC)augmentation method of a linear controller is proposed for air-breathing hypersonic vehicle(AHV)during inlet unstart.With the development of hypersonic flight technology,hypersonic vehicles have been gradually moving to the stage of weaponization.During the maneuvers,changes of attitude,Mach number and the back pressure can cause the inlet unstart phenomenon of scramjet.Inlet unstart causes significant changes in the aerodynamics of AHV,which may lead to deterioration of the tracking performance or instability of the control system.Therefore,we firstly establish the model of hypersonic vehicle considering inlet unstart,in which the changes of aerodynamics caused by inlet unstart is described as nonlinear uncertainty.Then,an MRAC augmentation method of a linear controller is proposed and the radial basis function(RBF)neural network is used to schedule the adaptive parameters of MRAC.Furthermore,the Lyapunov function is constructed to prove the stability of the proposed method.Finally,numerical simulations show that compared with the linear control method,the proposed method can stabilize the attitude of the hypersonic vehicle more quickly after the inlet unstart,which provides favorable conditions for inlet restart,thus verifying the effectiveness of the augmentation method proposed in the paper.

Distributed Control Technology for Air and Missile Defence Operations

This paper relates to accepted presentation at international conference Air and Missile Defence Technology,November 16-17,2022,London UK(day two),reflecting contents of the presentation slides.It describes applications of the patented and internationally tested Spatial Grasp Technology(SGT)and its Spatial Grasp Language(SGL)for Integrated Air and Missile Defense(IAMD).Based on holistic space navigation and processing by recursive mobile code self-spreading in distributed words,SGT differs radically from traditional management of large systems as consisting of parts exchanging messages.The dynamic network of SGL interpreters can be arbitrarily large and cover terrestrial and celestial environments as powerful spatial engines.The paper contains an example of tracking and destruction of multiple cruise missiles by self-evolving spatial intelligence in SGL using networks of radar stations.It also briefs the growing multiple satellite constellation in Low Earth Orbits(LEO)for potential IAMD applications.Starting from Strategic Defense Initiative(SDI)of the past and then briefing the latest project of Space Development Agency,the paper shows SGL solutions for discovery,tracking,and destroying ballistic missiles and hypersonic gliders with the use of collectively behaving constellations of LEO satellites.It also shows how to organize higher levels of supervision of groups of mobile chasers fighting multiple targets(both potentially as missiles or drones),by providing their global awareness even consciousness in SGL which can drastically improve their performance.The latest version of SGT can be implemented on any platforms and put into operation in a short time,similarly to its previous versions in different countries.

2023年国外航天领域发展综述

为及时、准确地了解2023年度国外航天领域的发展动向,对国外航天运输领域、弹道导弹领域以及高超声速技术领域的最新发展情况进行了全面梳理,涉及美、俄等各国航天领域的重点型号研发、飞行试验情况以及重大热点事件等,并通过综述分析对2024年国外航天领域的发展进行了展望。

外军导弹防御体系现状与发展研究

随着一体化防空反导理念的发展,美、俄等军事强国不断更新反导战略和反导体系发展规划,革新反导武器装备技术。通过分析美国反导政策和规划,分别从拦截弹作战性能提升、三位一体预警系统体系建设和一体化指控系统升级等方面,研究当前外军导弹防御体系发展现状和可运用的成熟技术,剖析反导试验成效,归纳未来导弹防御体系的发展趋势,为构建防空反导体系、提升反导作战能力提供启示和参考。

2023年国外空地导弹发展动态研究

2023年,世界军事强国大力投资并积极推动空地导弹的研发和实战化应用。本文对国外典型空地导弹的最新发展动态进行了总结,如美国的AGM-158联合空面防区外导弹(JASSM)、防区内攻击武器(SiAW)、AGM-183A高超声速导弹、AGM-182A高超声速攻击巡航导弹(HACM),英国的“矛”(SPEAR)导弹,俄罗斯的Kh-38多用途导弹、“匕首”高超声速导弹,以色列的“破冰者”(Ice Breaker)导弹等。同时对国外空地导弹的体系化协同作战、低成本系列化发展、电磁作战能力、高超声速领域激烈的竞争态势、打造数字工程生态系统等发展特点进行了总结和分析。

美国“面向作战人员的可扩展太空体系”未来发展分析

随着“面向作战人员的可扩展太空体系(PWSA)”进入部署阶段,美国将加速推动近地轨道卫星系统的发展,以确保在大国竞争中的绝对优势地位。跟踪研究了PWSA的发展背景、体系架构组成和部署现状等,分析了PWSA的发展特点。分析表明,美国将加速发展分布式、可扩展的近地轨道卫星星座,重点提升系统弹性,注重发展印太地区的覆盖能力,2030年前将实现全球导弹预警和跟踪能力。近地轨道卫星星座将提供低延时、高质量的跟踪数据,极大提升反导系统的作战能力和生存能力。

2023年国外高超声速领域发展综述

高超声速武器将使未来战争的样式产生深刻的变化,是当前装备科技领域博弈的焦点之一。对2023年美国、俄罗斯、法国、印度等世界主要国家在高超声速领域的重要发展动向进行梳理,分析其发展态势。最后,对国外高超声速技术的发展进行了总结。

引入虚拟目标的高超声速巡航导弹智能机动突防策略

针对高超声速巡航导弹机动突防时弹道偏离难以约束、突防策略对不同作战场景的泛化性能较差等问题,提出一种基于虚拟目标和上下文马尔可夫决策过程的智能机动突防决策算法。在以预定弹道为轴线的管状弹道包络面内选定多个静止的虚拟目标,采用深度强化学习算法对其相对预定弹道的位置参数进行决策;用比例导引律引导巡航弹依次攻击这些虚拟目标,在包络面内塑造出能满足突防要求的机动弹道。基于上下文马尔可夫决策过程,将针对单个作战场景的最优突防策略拓展到作战场景的概率分布上,提升突防策略对不同作战场景的适应性。仿真结果表明:该智能机动突防策略能在突防的同时约束弹道偏离,在拦截弹发射位置和机动能力发生变化时仍能保持良好性能。

美导弹防御体系发展情况和能力分析

美国近年来大力发展导弹防御系统,提出分层国土导弹防御、区域高超声速导弹防御等新型概念和方案,发布弹道导弹防御系统2.0新架构,致力于对弹道导弹和新型高超声速目标形成多层次、一体化的防御能力。针对美导弹防御系统的最新发展,研究了美导弹防御新型体系方案,梳理了美导弹防御重点武器装备,分析了美导弹防御关键能力,并进一步针对新域新质作战力量建设发展,从武器装备性能提升、体系协同作战、新型作战形态方面给出了武器装备的发展建议。

反高超声速导弹网格化拦截战法初步研究

高超声速导弹已成为大国博弈的尖端武器,对现有导弹防御系统造成了严重冲击。为应对高超声速导弹威胁,提出了一种分布式网格化拦截战法,有助于实现从分层防御到分布式防御的创新发展。该战法具有分布式作战、弹性作战的优势,满足反导作战的快速反应需求,容易在较大防御纵深上实现即时最优的拦截作战任务规划。给出了网格化部署模型和基于短期轨迹预报的拦截规划流程。在反高超声速导弹的想定场景下,对该战法进行了初步演示,并总结了战法原则。在天基组网探测支援下,该战法利用目标轨迹的短期预报,可有效应对高超声速目标的强机动威胁。

2023年美俄典型机载导弹发展动态与趋势分析

2023年,世界范围内机载导弹加速发展。本文对2023年美国和俄罗斯机载导弹领域的重大事件进行了梳理和分析,包括空空导弹、空面导弹、高超声速导弹和反辐射导弹等。美俄持续改进升级现役空空导弹并加速推进新型空空导弹发展,“突变”(MUTANT)新概念导弹项目引发广泛关注。美国系列化发展空面导弹并持续拓展挂装平台,F-35战斗机将集成AGM-158C空面导弹。俄罗斯推进机载高超声速武器实战应用,俄乌战争中“匕首”导弹战果显著。美国加速发展新型反辐射能力,AGM-88G导弹连续多次成功完成飞行试验,并将匹配集成P-8A和F-35等作战飞机。

Variable centroid control scheme over hypersonic tactical missile

This paper presents a brand-new tactical missile control scheme--variable centroid vector control according to the international highlight in the field of missile control and the research status of hypersonic missile control in China. Four critical problems related with the new control method are included: improving phase control in the spinning missile single-channel control; establishing variable centroid controlled spinning missile attitude dynamics equations; analyzing variable centroid control strategies and analyzing the stability of the controlled missile and implementing robust control. The achievements and results obtained are valuable and helpful to the theoretical explorations and engineering applications.

Prescribed fast tracking control for flexible air-breathing hypersonic vehicles:An event-triggered case

In this paper,a prescribed fast tracking control scheme is proposed for Flexible Airbreathing Hypersonic Vehicles(FAHV)subject to lumped disturbances and limited resources.To maintain tracking errors of velocity and altitude converge to a predefined region with a prescribed time and release the transient intense fluctuations encountered in classical Prescribed Performance Control(PPC)using a fast decaying rate,a tracking differentiator-based PPC is presented,where the reaching time and the maximum time differentiation of preselected envelopes can be regulated as a prior via fixing an acceleration factor,so that a guaranteed fast convergence speed can be realized with reduced oscillations.Besides,to avoid the excessive occupation of limited resources(energy and communication)and guarantee a remarkable tracking accuracy,switching event-triggered mechanisms are constructed for FAHV control realization,which provide a promising way to pursue a desired level of tracking performance with a low energy consumption.Subsequently,Uncertainty and Disturbance Estimators(UDE)and Sigmoid function-based Tracking Differentiators(STD)are employed to provide disturbance estimation and reference derivation with a low computational complexity.Finally,robust control laws are designed to compensate for the sampling error induced by event-triggered conditions,meanwhile Zeno phenomena can be effectively eliminated.The simulation results and comparisons validate the effectiveness of the proposed scheme.

Flight control for air-breathing hypersonic vehicles using linear quadratic regulator design based on stochastic robustness analysis

The flight dynamics model of air-breathing hypersonic vehicles （AHVs） is highly nonlinear and multivariable cou- pling, and includes inertial uncertainties and external disturbances that require strong, robust, and high-accuracy controllers. In this paper, we propose a linear-quadratic regulator （LQR） design method based on stochastic robustness analysis for the longitudinal dynamics of AHVs. First, input/output feedback linearization is used to design LQRs. Second, subject to various system parameter uncertainties, system robustness is characterized by the probability of stability and desired performance. Then, the mapping rela- tionship between system robustness and LQR parameters is established. Particularly, to maximize system robustness, a novel hybrid particle swarm optimization algorithm is proposed to search for the optimal LQR parameters. During the search iteration, a Chernoff bound algorithm is applied to determine the finite sample size of Monte Carlo evaluation with the given prohabilily levels. Finally, simulation results show that the optimization algorithm can effectively find the optimal solution to the LQR parameters.

2022年国外高超声速空面导弹发展动态研究

对2022年国外高超声速空面导弹的发展动态进行了总结和归纳,包括Kh-47M“匕首”高超声速导弹、Kh-95远程高超声速导弹、“锐利”高超声速导弹、“幼虫”-MD高超声速武器系统、AGM-183A高超声速导弹、高超声速攻击巡航导弹(HACM)、高超声速空射进攻性反水面目标导弹(HALO)、“啸箭”(Screaming Arrow)导弹、“牌王”(Gambit)导弹和“高超声速飞行2”(HyFly2)导弹,并对2022年国外高超声速空面导弹的研发、试验及作战等特点进行了分析。

Dynamic surface control and active disturbance rejection control-based integrated guidance and control design and simulation for hypersonic reentry missile

This paper proposes a novel integrated guidance and control(IGC)method combining dynamic surface control(DSC)and active disturbance rejection control(ADRC)for the guidance and control system of hypersonic reentry missile(HRM)with bounded uncertainties.First,the model of HRM is established.Second,the proposed IGC method based on DSC and ADRC is designed.The stability of closed-loop system is proved strictly.It is worth mentioning that the ADRC technique is used to estimate and compensate the disturbance in the proposed IGC system.This makes the closed-loop system a better performance and reduces the chattering caused by lumped disturbances.Finally,a series of simulations and comparisons with a 6-DOF non-linear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.