滑翔导弹末段多约束智能弹道规划

滑翔导弹末段飞行时空复杂度高、不确定性强、约束多,给弹道规划与制导算法带来了较大的建模和求解难度。针对这一问题,同时增大末段机动范围并提高弹道规划效率,本文提出一种利用连续型深度置信神经网络（Convolutional Deep Brief Networks,CDBN）预测机动能力、设计经由点状态实现末段多约束智能弹道规划的方法。过程中采用CDBN对机动能力进行在线预测,快速判定经由点状态的可行性,并且通过经由点状态智能设计,实现前后段能量的优化分配,扩大弹道机动包络;通过设计三角函数型弹目视线角实现末段弹道摆动机动,推导机动弹道最优末制导律对视线角进行跟踪,并调节机动频率以满足速度约束。仿真结果表明,CDBN相对BP网络具有更高的机动能力预测精度;本文所提智能弹道规划方法在满足末端速度约束的前提下,可以实现弹道摆动机动并大幅增加飞行包络。弹道规划能够在0.5 s内完成,满足工程应用的快速性要求。     

反坦克导弹三点法导引弹道仿真

导引规律是描述导弹质心运动应遵循的准则,它确定了弹道质心在空间的运动轨迹.在导弹的制导系统中,导引规律的作用是确定导弹飞行并命中目标的运动学弹道.采用一种合适的导引方法来改善导弹的制导性能,提高导弹的命中精度,一直是人们比较关心的问题.现主要通过对三点法导引规律的研究,分析各参数对导引弹道的影响.总结该法的优缺点,并提出了若干建议.     

Analytical impact time and angle guidance via time-varying sliding mode technique

To concretely provide a feasible solution for homing missiles with the precise impact time and angle, this paper develops a novel guidance law, based on the nonlinear engagement dynamics. The guidance law is firstly designed with the prior assumption of a stationary target, followed by the practical extension to a moving target scenario. The time-varying sliding mode (TVSM) technique is applied to fulfill the terminal constraints, in which a specific TVSM surface is constructed with two unknown coefficients. One is tuned to meet the impact time requirement and the other one is targeted with a global sliding mode, so that the impact angle constraint as well as the zero miss distance can be satisfied. Because the proposed law possesses three guidance gain as design parameters, the intercept trajectory can be shaped according to the operational conditions and missile׳s capability.To improve the tolerance of initial heading errors and broaden the application, a new frame of reference is also introduced. Furthermore, the analytical solutions of the flight trajectory, heading angle and acceleration command can be totally expressed for the prediction and offline parameter selection by solving a first-order linear differential equation. Numerical simulation results for various scenarios validate the effectiveness of the proposed guidance law and demonstrate the accuracy of the analytic solutions.     

Adaptive internal model guidance law for weaving maneuvering target

For the terminal phase guidance problem of the missile intercepting weaving maneuvering target, an adaptive internal model guidance laws in the three-dimensional (3-D) engagement space is proposed in this paper. The guidance law adopts the disturbance rejection theory by treating the target weaving maneuvering accelerations as external disturbance, which comprises of nominal part and adaptive part. The nominal part based on feedback linearization method ensures the whole guidance system stable and the adaptive part based on internal model principle is used to recover the disturbance signals on-line to reject the target maneuver asymptotically. The algorithm guarantees the whole guidance system with satisfying performance both in transient and steady state on the effect of target maneuver on guidance system. The stability analyses and theory proof are provided in this paper. At last, numerical simulations are carried out to illustrate the effectiveness of the proposed guidance law.     

弹道导弹中段突防弹道设计与验证

针对中段多脉冲弹道规划及评价问题,提出了一种新的弹道设计及评价方法。借鉴轨迹规划中节点搜索及扩展的思想,将多脉冲弹道的脉冲点火点视为节点,建立了多脉冲机动变轨模型。基于该模型,对突防弹道进行了设计及优化。运用"博弈论"的思想,在考虑敌方防御系统的探测机理、性能及部署基础上将敌方预测弹道与实际弹道的差值作为评价函数,以尽量降低敌方预测弹道的精度。最后,设计了导弹突防效能地面验证平台以验证所设计弹道的突防效率与弹道评价方法的有效性。选取了一个例子进行分析及验证,结果表明:相比最省能量弹道,设计的导弹防御系统对突防弹道的预测误差提高了5到15倍,达到了100~300km,飞行时间缩短了8.53%,而且规划时间不到140s。实验显示本文提出的弹道设计方法,能够在很短时间内规划出一条突防概率很高的弹道。     

Robust partial integrated guidance and control for missiles via extended state observer

A novel extended state observer (ESO) based control is proposed for a class of nonlinear systems subject to multiple uncertainties, and then applied to partial integrated guidance and control (PIGC) design for a missile. The proposed control strategy incorporates both an ESO and an adaptive sliding mode control law. The multiple uncertainties are treated as an extended state of the plant, and then estimate them using the ESO and compensate for them in the control action, in real time. Based on the output of the ESO, the resulting adaptive sliding mode control law is inherently continuous and differentiable. Strict proof is given to show that the estimation error of the ESO can be arbitrarily small in a finite time. In addition, the adaptive sliding mode control law can achieve finite time convergence to a neighborhood of the origin, and the accurate expression of the convergent region is given. Finally, simulations are conducted on the planar missile–target engagement geometry. The effectiveness of the proposed control strategy in enhanced interception performance and improved robustness against multiple uncertainties are demonstrated.     

采用伪谱法的再入飞行器最优反馈制导方法

将伪谱最优反馈控制理论应用于再入飞行器制导研究,使用伪谱法进行在线轨道重构,实时反馈更新当前轨道控制量迎角和倾斜角,达到实时最优反馈制导的目的,并采用无量纲化、弹性约束和自适应反馈更新等策略保证算法的实时性。再入飞行仿真表明,轨道重构可以满足实时性要求,阵风干扰下飞行器能达到所要求的终端约束条件,并且制导指令不会出现增加控制难度的抖动现象。     

采用伪谱法的再入飞行器最优反馈制导方法

将伪谱最优反馈控制理论应用于再入飞行器制导研究,使用伪谱法进行在线轨道重构,实时反馈更新当前轨道控制量迎角和倾斜角,达到实时最优反馈制导的目的,并采用无量纲化、弹性约束和自适应反馈更新等策略保证算法的实时性。再入飞行仿真表明,轨道重构可以满足实时性要求,阵风干扰下飞行器能达到所要求的终端约束条件,并且制导指令不会出现增加控制难度的抖动现象。     

Adaptive iterative learning control of a class of nonlinear time-delay systems with unknown backlash-like hysteresis input and control direction

This paper presents an adaptive iterative learning control scheme for a class of nonlinear systems with unknown time-varying delays and control direction preceded by unknown nonlinear backlash-like hysteresis. Boundary layer function is introduced to construct an auxiliary error variable, which relaxes the identical initial condition assumption of iterative learning control. For the controller design, integral Lyapunov function candidate is used, which avoids the possible singularity problem by introducing hyperbolic tangent funciton. After compensating for uncertainties with time-varying delays by combining appropriate Lyapunov-Krasovskii function with Young's inequality, an adaptive iterative learning control scheme is designed through neural approximation technique and Nussbaum function method. On the basis of the hyperbolic tangent function's characteristics, the system output is proved to converge to a small neighborhood of the desired trajectory by constructing Lyapunov-like composite energy function (CEF) in two cases, while keeping all the closed-loop signals bounded. Finally, a simulation example is presented to verify the effectiveness of the proposed approach.     

Non-singular terminal dynamic surface control based integrated guidance and control design and simulation

In this paper, a novel cascade type design model is transformed from the simulation model, which has a broader scope of application, for integrated guidance and control (IGC). A novel non-singular terminal dynamic surface control based IGC method is proposed. It can guarantee the missile with multiple disturbances fast hits the target with high accuracy, while considering the terminal impact angular constraint commendably. And the stability of the closed-loop system is strictly proved. The essence of integrated guidance and control design philosophy is reached that establishing a direct relation between guidance and attitude equations by “intermediate states” and then designing an IGC law for the obtained integrated cascade design model. Finally, a series of simulations and comparisons with a 6-DOF nonlinear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.     

Game optimal receding horizon guidance laws and its equivalence to receding horizon guidance laws

In this paper, a game optimal receding horizon guidance law (GRHG) is proposed, which does not use information of the time-to-go and target maneuvers. It is shown that by adjusting design parameters appropriately, the proposed GRHG is identical to the existing receding horizon guidance law (RHG), which can intercept the target by keeping the relative vertical separation less than the given value, within which the warhead of the missile is detonated, after the appropriately selected time in the presence of arbitrary target maneuvers and initial relative vertical separation rates between the target and missile. Through a simulation study, the performance of the GRHG is illustrated and compared with that of the existing optimal guidance law (OGL).     

Performance comparison of differential evolution techniques on optimization of feeding profile for an industrial scale baker’s yeast fermentation process

Differential evolution (DE) is one of the novel evolutionary optimization methods used for solving the problems that consist of nondifferentiable, nonlinear and multi-objective functions. In this presented work, the classical DE technique and its various versions, such as opposition based on differential evolution (ODE), adaptive differential evolution (ADE), adaptive opposition based on differential evolution (AODE) which is an advanced version of ODE, are presented to determine the optimal feeding flow profile of an industrial scale fed-batch baker’s yeast fermentation process. The main objective in any fed-batch fermentation process optimization is both to maximize the amount of the biomass at the end of the process and to minimize the ethanol formation during the process. Four different cases regarding the initial condition of the fermentation process were considered so as to evaluate the performances of proposed algorithms. Besides, two strategies of mutation and crossover operators, which are the most popular in DE’s applications, were utilized for performance comparison tests. The influence of initial seed value, initial condition of the process, and both of the mutation and crossover strategies have been investigated for all the different classic, opposition-based, self-adaptive and adaptive opposition-based mechanisms. To demonstrate the performance comparison of the of DE’s techniques, the experimental data collected from the fermentor with volume of 100 m³ are presented with the optimization results obtained by using all the interested DE techniques for the same initial conditions.     

Fuzzy logic sliding mode control for command guidance law design

Recently, the combination of sliding mode and fuzzy logic techniques has emerged as a promising methodology for dealing with nonlinear, uncertain, dynamical systems. In this paper, a sliding mode control algorithm combined with a fuzzy control scheme is developed for the trajectory control of a command guidance system. The acceleration command input is mathematically derived. The proposed controller is used to compensate for the influence of unmodeled dynamics and to alleviate chattering. Simulation results show that the proposed controller gives good system performance in the face of system parameters variation and external disturbances. In addition, they show the effectiveness of the proposed missile guidance law against different engagement scenarios where the results demonstrate better performance over the conventional sliding mode control.     

索系馈源支撑结构控制方法的研究

大射望远镜(LT)采用六根大跨度的钢索驱动馈源舱完成大范围扫描跟踪。针对系统中的索结构之间强耦合以及模型变结构的特点,基于非参数自适应技术,提了一种具有神经网络自适应反馈控制的方法。该方法对于馈源舱做空间轨迹跟踪时索质量时变具有一定的鲁帮性。LT50m模型实验结果表明馈源舱的定位精度达到1．5cm。     

Impact angle constrained three-dimensional integrated guidance and control for STT missile in the presence of input saturation

Considering a class of skid-to-turn (STT) missile with fixed target and constrained terminal impact angles, a novel three-dimensional (3D) integrated guidance and control (IGC) scheme is proposed in this paper. Based on coriolis theorem, the fully nonlinear IGC model without the assumption that the missile flies heading to the target at initial time is established in the three-dimensional space. For this strict-feedback form of multi-variable system, dynamic surface control algorithm is implemented combining with extended observer (ESO) to complete the preliminary design. Then, in order to deal with the problems of the input constraints, a hyperbolic tangent function is introduced to approximate the saturation function and auxiliary system including a Nussbaum function established to compensate for the approximation error. The stability of the closed-loop system is proven based on Lyapunov theory. Numerical simulations results show that the proposed integrated guidance and control algorithm can ensure the accuracy of target interception with initial alignment angle deviation and the input saturation is suppressed with smooth deflection curves.     

弹体飞行模拟及姿态显示

为降低成本、提高准确度,仿真技术成为导弹飞行研究的重要方法。本文研究了导弹飞行轨迹及姿态的解算,对飞行导弹进行了力学分析与建模。在分析导弹飞行特点和姿态参数求解算法的基础上,动态模拟了垂直平面内弹体飞行轨迹,并实时显示了弹体的姿态。本文实现了实验室环境下对导弹飞行过程的描述,为导弹实际飞行研究提供了参考。     

多目标跟踪算法在水质监测中的应用

针对活鱼水质监测系统中的活鱼跟踪中存在的问题,提出了一种基于视频的多目标跟踪算法,通过采用一种基于统计模型的背景建模方法得到了实验鱼缸的初始背景,并在活鱼目标检测跟踪过程中实时更新背景,在此基础上采用背景相减法和自适应图像二值化实现了活鱼运动目标的提取,并用连通区域分析提取活鱼的大小、质心等特征值,最后将卡尔曼预测器应用于基于运动特征的跟踪技术中,实现了活鱼的轨迹跟踪,提取到了活鱼的运动轨迹,最终达到了为后续的水质预警提供了可靠的轨迹数据的目的,所跟踪得到的活鱼运动轨迹数据是监测系统水质预警的重要基础。研究结果表明,该算法符合系统的实时性和准确性要求,能实现活鱼运动轨迹的准确快速跟踪。     

Multiobjective trajectory optimization of intelligent electro-hydraulic shovel

Multiobjective trajectory planning is still face challenges due to certain practical requirements and multiple contradicting objectives optimized simultaneously. In this paper, a multiobjective trajectory optimization approach that sets energy consumption, execution time, and excavation volume as the objective functions is presented for the electro-hydraulic shovel (EHS). The proposed cubic polynomial S-curve is employed to plan the crowd and hoist speed of EHS. Then, a novel hybrid constrained multiobjective evolutionary algorithm based on decomposition is proposed to deal with this constrained multiobjective optimization problem. The normalization of objectives is introduced to minimize the unfavorable effect of orders of magnitude. A novel hybrid constraint handling approach based on ε-constraint and the adaptive penalty function method is utilized to discover infeasible solution information and improve population diversity. Finally, the entropy weight technique for order preference by similarity to an ideal solution method is used to select the most satisfied solution from the Pareto optimal set. The performance of the proposed strategy is validated and analyzed by a series of simulation and experimental studies. Results show that the proposed approach can provide the high-quality Pareto optimal solutions and outperforms other trajectory optimization schemes investigated in this article.     

Determining probability of mission success when using deep penetration weapons

This paper presents the methodology for a system reliability analysis that can determine the probability of mission success of the destruction of buried concrete targets using deep penetration weapons. The success of the mission depends on various parameters, such as the properties of the target, the velocity and structural strength of the missile, the impact angle, etc., as well as other military scenarios. However, this paper only considers the structural design aspects. In this paper, analytical equations for the depth of penetration and buckling strength of the missile are used to demonstrate an efficient system reliability analysis methodology. These equations are also used to determine the sensitivity of mission success to various parameters. A discussion on the selection of parameters to maximize the mission success is also presented.     

Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint

The problem of impact angle control guidance for a field-of-view constrained missile against non-maneuvering or maneuvering targets is solved by using the sliding mode control theory. The existing impact angle control guidance laws with field-of-view constraint are only applicable against stationary targets and most of them suffer abrupt-jumping of guidance command due to the application of additional guidance mode switching logic. In this paper, the field-of-view constraint is handled without using any additional switching logic. In particular, a novel time-varying sliding surface is first designed to achieve zero miss distance and zero impact angle error without violating the field-of-view constraint during the sliding mode phase. Then a control integral barrier Lyapunov function is used to design the reaching law so that the sliding mode can be reached within finite time and the field-of-view constraint is not violated during the reaching phase as well. A nonlinear extended state observer is constructed to estimate the disturbance caused by unknown target maneuver, and the undesirable chattering is alleviated effectively by using the estimation as a compensation item in the guidance law. The performance of the proposed guidance law is illustrated with simulations.