ADRC FRACTIONAL ORDER PID CONTROLLER DESIGN OF HYPERSONIC FLIGHT VEHICLE

Active disturbance rejection controller（ADRC）uses tracking-differentiator（TD）to solve the contradiction between the overshoot and the rapid nature.Fractional order proportion integral derivative（PID）controller improves the control quality and expands the stable region of the system parameters.ADRC fractional order（ADRFO）PID controller is designed by combining ADRC with the fractional order PID and applied to reentry attitude control of hypersonic vehicle.Simulation results show that ADRFO PID controller has better control effect and greater stable region for the strong nonlinear model of hypersonic flight vehicle under the influence of external disturbance,and has stronger robustness against the perturbation in system parameters.

Output Feedback Dynamic Surface Controller Design for Airbreathing Hypersonic Flight Vehicle

This paper addresses issues related to nonlinear robust output feedback controller design for a nonlinear model of airbreathing hypersonic vehicle. The control objective is to realize robust tracking of velocity and altitude in the presence of immeasurable states, uncertainties and varying flight conditions. A novel reduced order fuzzy observer is proposed to estimate the immeasurable states. Based on the information of observer and the measured states, a new robust output feedback controller combining dynamic surface theory and fuzzy logic system is proposed for airbreathing hypersonic vehicle. The closedloop system is proved to be semi-globally uniformly ultimately bounded (SUUB), and the tracking error can be made small enough by choosing proper gains of the controller, filter and observer. Simulation results from the full nonlinear vehicle model illustrate the effectiveness and good performance of the proposed control scheme. © 2014 Chinese Association of Automation.

Adaptive dynamic surface control for air-breathing hypersonic vehicle

This paper describes an adaptive control approach for an air-breathing hypersonic vehicle. The control objective is to provide robust altitudes and velocity tracking in the presence of model uncertainties and varying disturbances. A fuzzy-neural disturbance observer is developed to estimate uncertainties and disturbances, and the adaptive controller is synthesized by the dynamic surface approach combing with the observer. The tracking error at the steady state can be guaranteed to converge to inside of a small residue set which the size of the set can be an arbitrary small value. Simulation results demonstrate the effectiveness of the presented approach.

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.

Improved Shuffled Frog Leaping Algorithm Optimizing Integral Separated PID Control for Unmanned Hypersonic Vehicle

To solve the flight control problem for unmanned hypersonic vehicles,a novel intelligent optimized control method is proposed.A flight control system based on integral separated proportional-integral-derivative(PID)control is designed for hypersonic vehicle,and an improved shuffled frog leaping algorithm is presented to optimize the control parameters.A nonlinear model of hypersonic vehicle is established to examine the dynamic characteristics achieved by the flight control system.Simulation results demonstrate that the proposed optimized controller can effectively achieve better flight control performance than the traditional controller.

Optimal speed of hypersonic cruise flight

A coupling frame of speed gain and maintain was suggested to assess the flight performance of hypersonic cruise vehicles(HCV).The optimal cruise speed was obtained by analyzing the flight performance measured by the ratio of initial boost mass to generalized payload.The performance of HCVs based on rockets and air-breathing ramjets was studied and compared to that of a minimum-energy ballistic trajectory under a certain flight distance.It is concluded that rocket-based HCVs flying at the optimal speed are a very competitive choice at the current stage.

高超声速飞行器热-结构试验若干关键技术

热-结构试验是高超声速飞行器研制过程中不可或缺的环节。本文在给出热-结构试验内涵与特征的基础上,结合热-结构试验典型科目介绍,呈现了热-结构试验体系总体架构,为全面了解热-结构试验提供参考;其次重点分析了当前热-结构试验中亟待突破的时变超高温热载实现、局部热载大梯度模拟以及时/频域载荷协同等7大关键技术。

动态自触发通信下多智能体输出反馈包容控制

针对群系统通信网络带宽受限问题,提出一种动态自触发通信下有向高阶非线性多智能体输出反馈包容控制方法。首先,针对群系统通信网络带宽受限问题,提出一种新型动态自触发通信机制。与传统事件触发通信机制相比,所提出的动态自触发通信机制具有更大的触发阈值,且无需连续监测系统状态信息,进一步节省系统通信资源和传感器资源。其次,为所有智能个体设计输出反馈控制协议,驱使所有跟随者收敛到由多个领导者围成的动态凸包中,从而实现网络的多领导者包容控制。最后,以高超声速飞行器群系统为例,验证了控制方法的有效性和理论分析的正确性。

测量噪声下的高超声速飞行器组合观测鲁棒控制

针对高超声速飞行器大包络飞行时,风场等外部干扰和测量噪声导致控制系统性能变差甚至失稳的问题,提出了一种基于状态观测的高超声速飞行器鲁棒控制策略。考虑噪声和外部干扰影响下系统状态受扰的问题,设计了扩张状态观测器(ESO)和自适应Kalman滤波器(AKF)的特殊组合,在统计特性未知的噪声和外部干扰影响下准确估计系统状态。其中,自适应Kalman滤波器用于滤除噪声,为扩张状态观测器提供不受噪声影响的状态估计,扩张状态观测器连续为自适应Kalman滤波器提供外部干扰估计。基于系统状态估计设计线性高斯二次型控制器,实现高超声速飞行器精确轨迹跟踪。最后,通过仿真验证了该方法在测量噪声及风干扰影响下的鲁棒跟踪能力。

带有时间约束的多飞行器协同轨迹规划

面向多个高超声速飞行器在指定时间到达指定区域的场景,本文提出了一种带有时间约束的多飞行器协同轨迹规划方法.首先,通过解决飞行器再入飞行时间与横向机动之间的耦合问题,基于二元牛顿迭代法设计了一种考虑飞行时间约束和航程约束的纵向轨迹规划方法.然后,在横向平面内基于一种边界可调式的航向角偏差走廊实现了飞行器的横向机动,同时,设计了一种补偿更新策略不断迭代直至得到满足飞行时间约束的三维轨迹.在此基础上,分析了飞行器的飞行能力并给出了一种飞行器的协同飞行时间、终端高度和飞行航程的确定方法.最后,通过多飞行器协同飞行的仿真结果表明,本文的方法能够得到多飞行器满足飞行时间和终端约束的三维轨迹,并具有良好的计算精度.同时,蒙特卡洛仿真表明该协同轨迹规划方法对各项扰动具有较强的鲁棒性.

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。

超燃冲压发动机用SCO_(2)闭式回热布雷顿循环的热电转换系统性能分析

针对高超声速飞行器的供电和热防护需求,本文提出了一种基于超临界二氧化碳(SCO_(2))闭式回热布雷顿循环(RCBC)的热电转换系统,建立了一个由超燃冲压发动机燃烧室、壁面冷却通道和SCO_(2),RCBC组成的耦合模型来评估系统性能。对比了燃烧室与冷却通道耦合和不耦合的差距;分析了冷却流体进人冷却通道时的进口参数对系统热防护以及供电的影响。结果表明,热电转换系统通过将部分热量转化为电能,在对发动机进行热防护的同时,可以为高超声速飞行器提供25.14kW的电能。

采用利希滕贝格图的高超声速飞行器轨迹优化

针对复杂约束条件下高超声速飞行器再入轨迹优化问题,提出一种混合算法进行求解,以解决现有轨迹优化方法对初值的强依赖性以及易陷入局部最优等问题。将高超声速飞行器再入轨迹优化建模成一个非线性规划问题,并设计双层优化结构进行求解。上层中,提出一种基于利希滕贝格图的自适应分段利希滕贝格算法(Adaptive piecewise Lichtenberg algorithm,APLA),为高斯伪谱法提供良好的初值。APLA通过引入拉丁超立方体抽样提升算法初始触发点的效能,引入全局至局部搜索分段策略及自适应因子提高算法收敛速度和收敛精度,改善算法易陷入局部最优等情况。下层中,高斯伪谱法在最优解附近具有较好的收敛速度和较高收敛精度,因此使用高斯伪谱法以加快搜索过程,提升解的全局最优性。综上,提出再入轨迹优化混合算法(APLA_GPM),实现对高超声速飞行器再入轨迹优化问题快速、准确求解。仿真结果表明,APLA_GPM在高超声速飞行器再入轨迹优化方面具有更快的收敛速度、更高的精度以及更强的鲁棒性。

吸气式高超声速机动飞行样式及其关键技术分析

机动飞行性能是确保吸气式高超声速飞行器实现多种应用的关键能力之一,本文重点对吸气式高超声速飞行器机动能力特点进行研究。首先分析了国外吸气式高超声速飞行器的发展趋势,就其典型机动能力水平和机动样式进行了初步分析,以美国当前典型高超声速导弹项目为例,梳理了吸气式高超声速飞行器的典型机动应用样式。在此基础上,从总体设计、气动外形、飞发一体、制导控制、多场耦合等方面,梳理分析了确保和提升吸气式高超声速飞行器机动能力的关键支撑性技术。

Adaptive Performance-Constrained Synchronization Control for Hypersonic Flight Vehicle Swarms: A Novel Finite-Time Convergence Protocol Methodology

This paper proposes a novel neural adaptive performance-constrained synchronization tracking control algorithm for multiple hypersonic flight vehicles(HFVs),which are subject to actuator faults and full-state constraints.The proposed method is based on advanced Lyapunov finite-time stability theory and a sophisticated backstepping design scheme.The longitudinal model of HFV is converted into velocity and altitude subsystems through functional decomposition.Our method presents three significant contributions over the existing state-of-the-art approaches:(a)ensuring finite-time convergence of HFVs systems by guaranteeing that the setting time is lower bounded by a positive constant that is related to the initial states;(b)utilizing a tan-type Barrier Lyapunov function(BLF)to ensure that the synchronization tracking errors of velocity,altitude,flight path angle,angle of attack,and pitch angle rate are maintained within certain performance bounds;and(c)designing a neural adaptive control algorithm and adaptive parameter laws by combining the backstepping design technique and radial basisfunction neural networks(RBFNNs)to handle unknown actuator faults and modeling uncer-tainties.Finally,comparative simulations are conducted to validate the efficacy of the proposed scheme.

基于深度学习的高超声速飞行器运动行为识别

高超声速飞行器具有机动大、速度高、航程远、威胁强等特点,已成为各大国重点发展的武器装备,识别其运动行为能为防御和拦截提供有力的技术支持。本文对有禁飞区等复杂约束条件下的高超声速飞行器运动行为识别问题开展研究:首先通过分析高超声速飞行器的运动特点,建立能够充分描述其行为模式的参数化运动方程;然后基于优化思想求解有禁飞区等复杂约束条件下的航迹规划问题,构建其数据集;最后基于深度学习方法设计高超声速飞行器运动行为识别算法。试验结果表明:所设计的识别算法能够实现对高超声速飞行器运动行为的识别,且具有一定的泛化能力,可为后续防御决策提供一定的参考。

高超声速飞行器预设性能抗饱和容错控制方法

针对高超声速飞行器飞行中所面临的扰动与不确定性、执行机构部分失效故障以及输入饱和问题,提出了一种预设性能抗饱和容错控制方法。在控制器设计过程中,首先利用扩张状态观测器估计扰动与不确定性,并在控制器中进行补偿;然后,设计了一种新型有限时间收敛的预设性能控制方案,并与自适应控制相结合解决执行机构部分失效问题;最后,通过加入辅助系统解决了输入饱和问题。仿真结果表明:所设计的控制方案可以有效降低故障影响,提高跟踪误差收敛速度,限制输入量变化范围。

Robust Coordinated Control for a Type of Hypersonic Aircraft

We investigate couplings between variables of attitude dynamics for a hypersonic aircraft,and present a nonlinear robust coordinated control scheme for it.First,we design three kinds of coordinated factors to restrain the strong couplings.Then,we use projection mapping to estimate the uncertain nonlinear functions of the aircraft.Combining the coordinated factors and the designed control laws,we obtain a coordinated torque and assign it to the control deflection commands by using the allocation matrix.A stability analysis demonstrates that all the signals of the closed-loop system are uniformly and fully bounded.Finally,the robust coordinated performance of the designed scheme is verified through numerical simulations.

多源干扰下高超声速飞行器自主精细控制

从高超声速飞行器自主精细控制需求出发,研究了器件失效退化、烧蚀变质心、燃料快速消耗等多源干扰与不确定性表征以及飞行器深耦合系统建模方法,提出了干扰在线预示、风险在线预警和强抗扰控制策略,并梳理了若干值得深入探索的前沿科学问题。强抗扰控制的设计目的是通过干扰在线预示、风险在线预警和柔性重构,赋予高超声速飞行器极端环境下强自主、强适应、强生存等智能行为能力。仿真测试结果表明,与传统自抗扰控制方法相比,强抗扰控制方法可显著提升飞行器极端环境下的自主性、适应性和可靠性。

跨流域高速飞行器气动设计研究现状及思考

针对跨流域空气动力学理论的不完善、多物理非平衡效应耦合的跨流域流场高精度预示模型缺乏、大空域和宽速域流动控制难度大等问题,本文从气动布局、气动预示和气动优化三个方面对跨流域高速飞行器气动设计的研究现状进行了回顾,对气动设计中涉及到的难点和关键问题进行了思考,并提出了相关发展建议。