Design methodology of a mini-missile considering flight performance and guidance precision

The design of mini-missiles(MMs)presents several novel challenges.The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision.The miniaturization of the size of MMs makes the design of the guidance,navigation,and control(GNC)have a larger-thanbefore impact on the main-body design(shape,motor,and layout design)and its design objective,i.e.,flight performance.Pursuing a trade-off between flight performance and guidance precision,all the relevant interactions have to be accounted for in the design of the main body and the GNC system.Herein,a multi-objective and multidisciplinary design optimization(MDO)is proposed.Disciplines pertinent to motor,aerodynamics,layout,trajectory,flight dynamics,control,and guidance are included in the proposed MDO framework.The optimization problem seeks to maximize the range and minimize the guidance error.The problem is solved by using the nondominated sorting genetic algorithm II.An optimum design that balances a longer range with a smaller guidance error is obtained.Finally,lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.

APPLICATION OF HYBRID AERO-ENGINE MODEL FOR INTEGRATED FLIGHT/PROPULSION OPTIMAL CONTROL

The real-time capability of integrated flight/propulsion optimal control （IFPOC） is studied. An appli- cation is proposed for IFPOC by combining the onboard hybrid aero-engine model with sequential quadratic pro- gramming （SQP）. Firstly, a steady-state hybrid aero-engine model is designed in the whole flight envelope with a dramatic enhancement of real-time capability. Secondly, the aero-engine performance seeking control including the maximum thrust mode and the minimum fuel-consumption mode is performed by SQP. Finally, digital simu- lations for cruise and accelerating flight are carried out. Results show that the proposed method improves real- time capability considerably with satisfactory effectiveness of optimization.

ENERGY STATE APPROACH TO THE INTEGRATED FLIGHT PERFORMANCE MANAGEMENT OF COMMERCIAL AIRCRAFT

The integrated aircraft flight performance management techniques are discussed in this paper based on the point-mass energy state approximation principle. The flight performance optimization algorithms, developed with energy state approximation approach, are first introduced, the functionally integrated flight path/speed control system, so called total energy control system (TECS), is then discussed, and the guidance technique and algorithms, which relate the performance optimization results directly with the TECS, are analyzed and developed. Digital simulation results for a specific transport aircraft model demonstrate the satisfactory performances of the resulted flight performance management system.

FLIGHT／THRUST INTEGRATED CONTROL USINGH∞SYNTHESIS IN AUTOMATIC CARRIER LANDING

The landing task of an aircraft under low aerodynamic pressure on carrier requires precise airplane control,A flight/thrust integrated control system(FTICS)with constant ad,actual angle of attack,is developed using LMI-based H∞synthesis.The typical single input/outputspecifications are translated into the weighting functions of an H∞output-feedback synthesis problem.The motiva-tion of the work is to improve the key performance of dy-namic tracking and air disturbance attenuation.The FTICS can keep the attitude andgle and the path angle un-changeable as the airplane is passing through the ramp at which the tracking radar doesnot work and the guidance signal is terminated.For engineering application,an or-der-reduction method of the H∞controller is also pro-posed,Simulational results indicate that the system satis-fies the design requirements quite well.

THE EIGENVALUE SENSITIVITY ANALYSIS AND DESIGN FOR INTEGRATED FLIGHT/PROPULSION CONTROL SYSTEM

In this paper, sensitivity approaches are taken to analyze and design an integrated flight propulsion control system where the interaction between subsystems direitly affects the stability property and handling performances of the aircraft. The eigenvalue sen sitivity approach is employed to study the effect of coupling parameters on system stability and gain sensitivity approach is used to direct the reduced states feedback suboptimal control system design. Simulation results show that the integrated flight propulsion control system designed by sensitivity approaches is of good performance.

Safety flight envelope calculation and protection control of UAV based on disturbance observer

In this paper,as for the unmanned air vehicle(UAV)under external disturbance,an attainable-equilibrium-set-based safety fight envelope(SFE)calculation method is proposed,based on which a prescribed performance protection control scheme is presented.Firstly,the existing definition of the SFE based on attainable equilibrium set(AES)is extended to make it consistent and suitable for the UAV system under disturbance.Secondly,a higher-order disturbance observer(HODO)is developed to estimate the disturbances and the disturbance estimation is applied in the computation of the SFE.Thirdly,by using the calculated SFE,a desired safety trajectory based on the time-varying safety margin function and first-order filter is developed to prevent the states of the UAV system from exceeding the SFE.Moreover,an SFE protection controller is proposed by combining the desired safety trajectory,backstepping method,HODO design,and prescribed performance(PP)control technique.In particular,the closed-loop system is established on the basis of disturbance estimation error,filter error,and tracking error.Finally,the stability of the closed-loop system is verified by the Lyapunov stability theory,and the simulations are presented to illustrate the effectiveness of the proposed control scheme.

梯度风场滑翔仿生飞行器设计与仿真

将信天翁从梯度风场中获取能量滑翔数千英里的飞行策略应用在飞行器上是突破飞行器续航瓶颈的重要方法之一。本文结合信天翁身体特性和飞行策略,设计了一种具有信天翁仿生外形、气动布局和控制方式的仿信天翁飞行器,巡航时升阻比为梯形翼飞行器的1.13倍,最大可达梯形翼飞行器升阻比的1.31倍,通过翼尖变形阻力最高可减小12%,翼根载荷减小35%。根据信天翁在滑翔时不时扑动翅膀的行为提出了间歇动力梯度风滑翔方法,对仿信天翁飞行器进行了风梯度滑翔操控性能仿真。结果表明实际飞行路径与风梯度滑翔路径的误差小于5%,能量消耗为匀速飞行的51.5%,验证了间歇动力梯度风滑翔策略的合理性。

一种组合动力飞行器模态转换过程轨迹优化与控制方案

为应对组合动力飞行器涡轮/冲压发动机模态转换过程中容易出现的推力陷阱问题,开展了组合动力飞行器模态转换阶段飞行/推进一体化保护控制研究。该研究利用组合动力爬升段飞行轨迹优化方法,解决模态转换过程中组合发动机总推力无法满足平飞加速需求的推力陷阱问题。结合轨迹线性化控制方法,完成了宽速域飞行器/发动机一体化轨迹跟踪控制设计,利用迎角、油门等变量的协同调节实现轨迹跟踪控制。仿真结果表明,轨迹优化策略能够在一定程度上克服模态转换过程中的推力不足问题,一体化轨迹线性化控制方法可以有效实现爬升轨迹跟踪,避免模态转换过程对组合动力飞行器飞行任务造成的不利影响。

空地一体化测绘多无人机飞行协同控制方法

针对多无人机在协同编队飞行过程中通信信息利用率低,导致无人机轨迹规划效果差、效率低等问题,本文提出了一种空地一体化测绘多无人机飞行协同控制方法。利用A*算法改进一致性算法,对多个共同飞行的无人机实行任务分配,通过改进的一致性算法实行轨迹规划。根据无人机航向角、飞行高度和速度等信息,对无人机进行编队控制,实现多无人机飞行协同控制。实验结果表明:所提方法避障效果较优,适用于各类对多无人机控制精度要求较高的工作。

巡飞弹航迹规划与飞行控制方法发展

巡飞弹是无人机技术与弹药技术结合的产物,可实现战场态势感知、精确打击、信息支援等功能,是未来信息化作战的重要武器之一。介绍巡飞弹的定义组成、分类方法、作战功能、型号发展、战场应用等情况;阐述巡飞弹航迹规划方法的发展现状和未来趋势,包括传统规划方法、智能规划算法和集群规划算法等;对巡飞弹飞行控制的关键技术,包括制导、姿控和导航技术的发展现状和未来趋势进行了介绍,其中的制导技术包括巡飞段跟踪制导、俯冲段末制导和多弹协同制导等;展望了巡飞弹未来的发展方向。

主动噪声控制技术在涡扇飞机飞行试验中的应用研究

为研究主动噪声控制技术在涡扇飞机真实飞行环境下的作用效果,基于自适应滤波算法设计了一套主动降噪系统,并在与航线飞机舱内环境完全相同的试飞机上集成安装,挑选航线爬升和不同巡航高度典型飞行试验工况开展试飞试验,通过对试飞数据的分析结果表明:在飞机复杂的飞行环境及舱内声场环境下,主动降噪系统在目标降噪区域仍有明显的降噪效果,且降噪效果与基础噪声有较大的关系,通常是往空间噪声声压级趋于一致的方向调整,基础噪声越大,降噪效果越好;且对低频的噪声控制效果更为稳定,效果更好;并对主动降噪系统在涡扇飞机上的布局方案形成指导建议。

时间约束三维超螺旋滑模制导控制一体化方法

针对飞行器时间约束制导问题,提出了一种新型三维制导控制一体化方法。为满足大前置角及大期望到达时间下时间约束制导的需要,提出了一种新型滑模面,并证明了滑模运动时前置角的渐近收敛特性。在该滑模面的基础上,基于超螺旋算法和反步法,提出了有限时间稳定的制导控制一体化控制律,保证李普希茨有界扰动下的鲁棒,且控制量连续,其有限时间收敛特性通过李雅普诺夫稳定性理论得到证明,其有效性通过数值仿真得到了验证。

MAGIC CARPET着舰控制的稳定性

魔毯(MAGIC CARPET)是美国最近几年非常成功的舰载机着舰控制技术,是未来主要的着舰方式。研究了MAGIC CARPET控制的稳定性。首先,分析MAGIC CARPET着舰和常规着舰的控制结构。然后,进行人在环实时仿真实验,实验有MAGIC CARPET控制和常规控制两组,每组中又分油门不动和自动油门接通两种情况。实验显示稳定能力(轨迹稳定性、轨迹可控性、速度稳定性、迎角稳定性),从高到低的排序是:MAGIC CARPET控制(正常有自动油门情况)?MAGIC CARPET控制(油门不动情况)?常规控制(正常有自动油门)?常规控制(油门不动情况),可见MAGIC CARPET的稳定性能非常优秀。最后,从D-V曲线、信号流图、复域等多角度,综合分析了MAGIC CARPET控制和常规控制的稳定性机理。研究结果可为飞机着舰和直接力控制等方面提供参考。

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。

基于管制指令的飞行冲突调配评估方法的研究

通过分析飞行冲突的预测与调配过程,根据飞行计划内的航迹和按调配规则调配后的航迹的对比明确飞行冲突危险指数概念,以此构建以有效性、准确性和及时性三个指标为基准的飞行冲突调配评估指标体系和评估指标的计算过程。飞行冲突评估指标体系及对比分析方法对飞行冲突的调配过程进行了量化,提高了决策结果的可信度,实现了在飞行冲突调配过程中对管制指令的分析。

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。

自动飞行系统飞行模式操作验证方法研究

现代民用飞机的自动飞行控制系统是主要的人机交互系统之一,其飞行模式操作控制功能由两大物理部分组成:FMCP硬件与自动飞行控制软件。对于复杂的人机交互功能的验证,需要采用面向开发过程的模型验证方法,首先由系统功能层级到功能模块层级逐级分解飞行模式操作控制功能开发架构,进而从功能模块层级到系统功能层级自下而上设计飞行模式操作控制功能验证架构,最后针对功能验证架构中的集成模型测试阶段,以FMCP速度视窗功能为例,通过对所有相关的人机操作进行分类定义,分别定义了速度目标值的状态转换与动作响应,进而针对定义梳理出完整的速度目标值状态转换与动作响应矩阵,矩阵中的每一个表格均对应着速度目标值的状态转换或者动作操作及其对应的响应情况。为自动飞行模式操作控制的集成模型验证提供了参考。

基于业财融合的企业内部控制体系建设研究

为解决现代企业运营发展难题,文章将从业财融合角度出发,围绕企业内部控制体系建设展开研究,重点阐述了业财融合在企业内部控制中的作用,进一步分析了业财融合下企业内部控制的要点内容,从业财融合视角提出几点针对性的措施,旨在发挥业财融合导向价值,完善企业内部控制管理机制,推进业务与财务有机融合,促进企业未来发展。

Control performance simulation and tests for Microgravity Active vibration Isolation System onboard the Tianzhou-1 cargo spacecraft

The Microgravity Active vibration Isolation System(MAIS),which was onboard China’s first cargo-spacecraft Tianzhou-1 launched on April 20,2017,aims to provide high-level microgravity at an order of 10^(-5)–10^(-6)g for specific scientific experiments.MAIS is mainly composed of a stator and a floater,and payloads are mounted on the floater.Sensing relative motion with respect to the stator fixed on the spacecraft,the floater is isolated from vibration on the stator via control forces and torques generated by electromagnetic actuators.This isolation results in a high-level microgravity environment.Before MAIS was launched into space,its control performance had been simulated on computers and tested by air-bearing platform levitation and aircraft parabolic flight.This article first presents an overview of the MAIS’s hardware system,particularly system structure,measurement sensors,and control actuators.Its system dynamics,state estimation,and control laws are then discussed,followed by the results of computer simulation and engineering tests,including the test of the six-degree-of-freedom motion by aircraft parabolic flight.Simulation and test results verify the accuracy of the control strategy design,effectiveness of the control algorithms,and performance of the entire control system,paving the way for operation of MAIS in space.This article also presents the steps recommended for the control performance simulation and tests of MAIS-like devices.These devices are expected to be used on China’s Space Station for various scientific experiments that require a high-level microgravity environment.

Overview of control-centric integrated design for hypersonic vehicles

Hypersonic vehicles(HSVs)exhibit significant advantages over other vehicles,including the wide range of velocity and large airspace types,and these features have contributed to the rapid development of HSVs in the last 20 years.Moreover,hypersonic technologies have become a multidisciplinary research topic in the fields of aerodynamics,propulsion,structure,material,and control.Different types of re-entry gliding,air-breathing cruise,and aerospace vehicles have been designed to realize ambitious tasks,which in turn influenced the technological advancements and process change in the military.This paper summarizes the control-oriented integrated design of HSVs.First,the status of current research on the distinct characteristics and technique issues of HSVs is introduced.Then,the progresses made on complex modeling,guidance and control,and trajectory optimization are elaborated to exhibit the significant research interest in hypersonic technologies.The control-integrated design of HSVs is emphasized to solve the multidisciplinary design problems associated with the model and its control and trajectory.Various strategies regarding the multidisciplinary optimization design are also proposed to solve the integrated design problem.Finally,suggestions are provided for the control-oriented integrated design of HSVs.