含攻击角度约束的三维制导控制一体化鲁棒设计方法

针对具有攻击角度约束的STT飞行器对象,提出了一种三维制导控制一体化鲁棒设计方法.首先,基于某些可行性简化原则,推导出面向三维制导控制一体化设计的非线性数学模型.然后,针对一类多变量非线性系统,通过引入控制补偿项,提出了一种鲁棒动态逆设计方法.结合鲁棒动态逆和动态面控制方法,完成了制导控制一体化鲁棒算法的设计.仿真结果表明,所提出的三维制导控制一体化算法可保证飞行器的稳定飞行和精确制导,并且满足攻击角度的约束要求.此外,该方案具备针对参数不确定性和等效干扰的强鲁棒性能.     

基于Nussbaum增益滑模自适应控制的 导弹制导控制一体化设计

采用Nussbaum增益滑模自适应控制方法解决导弹制导控制一体化设计问题. 充分考虑一体化模型具有通道间耦合、气动建模不确定性、气动参数摄动和目标机动引起的干扰等特点, 基于自适应控制对未知量的辨识能力和滑模控制的抗干扰能力, 以及Nussbaum增益控制对系数不确定系统所具有的较好的控制能力, 设计Nussbaum增益滑模自适应控制律, 并证明系统的稳定性. 仿真结果验证了所提出方法的有效性.     

基于加幂积分方法的制导控制一体化设计

针对高超声速飞行器纵向制导控制一体化设计问题展开研究.首先建立纵向制导与控制系统一体化设计模型;然后结合非线性干扰观测器与加幂积分方法设计制导与控制一体化算法,并借助相关基础理论证明级联系统是全局有限时间稳定的.所提出的方法可以使制导与控制系统协调配合,更充分地利用飞行器控制能力.通过与反步滑模制导控制一体化设计方法进行对比仿真,验证了该方法有效且更具优势,并通过模拟外扰及参数拉偏情况下的仿真验证了所提出方法亦具备较强的鲁棒性.     

固定翼无人机自动着陆的一体化制导控制

本文基于制导控制一体化方法的思想,将滑模变结构控制和自抗扰控制技术结合于动态面控制结构中,提出一种固定翼无人机自动着陆方法.在建立六自由度无人机模型、无人机和目标点间的相对视线角度模型的基础上,在动态面控制框架下加入滑模变结构控制来设计制导控制一体化方法.在此过程中加入自抗扰控制技术,提高了系统对未建模部分、参数的不确定性和外界干扰的鲁棒性,并抑制了滑模变结构控制的抖振.该方法使得无人机在平稳地飞向目标点的同时能够满足着陆视线角度的约束.文中详细论述设计思想和设计方法,最后通过仿真验证说明本文方法的有效性.     

空地微型导弹导引与控制一体化设计与仿真

以某空地微型导弹为研究对象,研究了导引控制一体化控制器设计问题.为了实现导弹导引控制一体化,建立了俯仰、偏航通道的一体化模型,并将其转化为具有一般形式的含未知有界不确定性的子系统.采用自适应滑模控制方法设计了非线性一体化控制律.通过导弹空对地攻击的六自由度非线性数字仿真验证了导弹导引控制一体化控制算法的可行性、有效性.所设计的控制器一方面能保证导弹自身姿态的稳定性,另一方面具有较高的制导精度.对微型导弹的研制具有一定的参考意义.     

带落角约束的高超声速飞行器一体化制导控制

本文针对高超声速飞行器高速俯冲过程中的质心运动与绕质心运动之间存在强耦合的特点,提出了一种基于全量耦合模型的满足落角约束的一体化制导控制方法.首先建立基于视线角的飞行器与目标的相对运动方程和绕质心运动方程,通过微分同胚处理得到一体化制导控制模型.接着采用自适应块动态面反演方法提出了一体化制导控制方法.该方法充分考虑了飞行器质心运动与绕质心运动之间的耦合作用,显著提高高超声速飞行器高速俯冲过程中的整体控制性能.本文提出的一体化制导控制方法能使得飞行器闭环系统的状态一致最终有界,且视线角速率的界可以达到任意小.最后,通过仿真结果验证了全量耦合一体化制导控制方法的有效性.     

超声速巡航弹俯冲攻击制导控制一体化设计

研究巡航导弹俯冲优化控制问题,针对超声速巡航导弹俯冲攻击要求,为了使战斗部发挥最大毁伤效果,运用变结构控制理论,设计了导弹纵向平面一体化制导控制系统.联立弹目相对运动方程和导弹弹体动力学方程,建立了导弹控制模型.选用零控脱靶量滑模切换面,并将目标机动考虑成有界扰动,使控制具有较强的自适应性和对目标机动性.数值仿真表明,设计的一体化制导控制系统能满足俯冲攻击的脱靶量和落角的要求,验证了方法有效.与传统的制导控制分开设计比较,采用所提出的一体化制导控制系统末段状态的变化更平缓,能获得更小的脱靶量,具有机动攻击目标的能力,并满足设计的要求.     

适用于制导控制一体化的模糊滑模方法

为了提高打击大机动目标命中率、机动性和燃油利用率, 设计一种适用于制导控制一体化的模糊滑模方法. 建立拦截导弹制导控制一体化模型, 选取零控脱靶量作为滑模面, 将制导律嵌入控制器的设计中, 并将运动学关系与 动力学特性有机融合. 在滑模控制器中加入模糊环节, 有效克服了滑模方法的抖振问题. 目标蛇形机动的弹道仿真结果表明, 所提出方法可以有效提高系统各方面的性能.

     

具有结构不确定性的时滞系统的闭环鲁棒预测控制器

针对具有结构不确定性的时滞系统,设计了闭环鲁棒预测控制算法.该控制算法基于控制不变集方法,通过采用双模控制和闭环控制策略,增加了控制设计的自由度,进而扩大了系统的初始可行域并能获得较优的控制性能.仿真结果验证了该方法的有效性.     

终端约束条件下末端制导律研究综述

现代战场环境的日益复杂化和激烈化,多约束条件下制导律的设计成为研究热点.本文首先介绍了末端制导律的研究背景和研究意义,概述了由于环境的复杂,目标的高机动性,及飞行器运动的非线性、强耦合性和多时变性性等因素带来制导律设计上的困难.然后对具有多终端约束条件下末端制导律的设计方法进行分类,将其分为单终端约束制导律和多终端约束制导律,并对具有终端角度、弹着时间、和终端速度的某一种或几种约束的制导律方法进行归纳总结.最后对下面4种末端制导律的发展趋势进行了展望:三维制导律、制导控制一体化、多飞行器协同制导和多模复合末制导.     

Adaptive dynamic surface control for integrated missile guidance and autopilot

Integrated guidance and control for homing missiles utilizing adaptive dynamic surface control approach is considered based on the three channels independence design idea. A time-varying integrated guidance and control model with unmatched uncertainties is first formulated for the pitch channel, and an adaptive dynamic surface control algorithm is further developed to deal with these unmatched uncertainties. It is proved that the proposed feedback controller can ensure not only the accuracy of target interception, but also the stability of the missile dynamics. Then, the same control approach is further applied to the control design of the yaw and roll channels. The 6-degree-of-freedom (6-DOF) nonlinear missile simulation results demonstrate the feasibility and advantage of the proposed integrated guidance and control design scheme.     

Adaptive Integrated Guidance and Control Based on Backstepping and Input‐to‐State Stability

This paper presents an approach of integrated guidance and control (IGC) design for interception of maneuvering targets (evaders). An IGC model with uncertainties in the pitch plane is formulated, and, by adopting a backstepping scheme, an adaptive nonlinear IGC approach is developed. Theoretical analysis shows that the design approach makes the line‐of‐sight (LOS) rate be input‐to‐state stable (ISS) with respect to target maneuvers and missile model uncertainties, and the stability of the missile dynamics can be guaranteed as well. The numerical simulation confirms the effectiveness of the proposed design approach.     

基于拟连续高阶滑模的高超声速飞行器再入姿态控制

考虑模型参数不确定和外界干扰对再入制导控制性能的影响,基于拟连续高阶滑模控制策略对高超声速飞行器的再入制导控制问题进行了研究.首先,给出再入制导指令的设计过程.其次,基于再入飞行特性对模型进行简化,获得面向控制的姿态模型,在此基础上,通过引入新的控制变量,设计解耦滑模面,实现姿态间的解耦.再次,为了削弱控制抖振,通过引入虚拟控制,对系统进行增广,基于齐次性理论设计拟连续三阶滑模再入姿态控制器,确保系统在有限时间实现对制导指令的稳定跟踪.最后,六自由度再入飞行器的制导控制一体化仿真结果表明,本研究给出的控制策略在不影响系统鲁棒性的同时,能够实现对标称轨迹和再入姿态的综合控制.     

Discrete terminal sliding mode repetitive control for a linear actuator with nonlinear friction and uncertainties

A robust discrete terminal sliding mode repetitive controller is proposed for a class of nonlinear positioning systems with parameter uncertainties and nonlinear friction. The terminal sliding mode control (TSMC) part is designed to improve the transient characteristics of the system, as well as the robustness against parameter uncertainties, nonperiodic nonlinearities, and disturbances. The repetitive control (RC) part is then integrated to eliminate the effects of the periodic uncertainties present in the system. Moreover, a pure phase lead compensator is incorporated into the RC to improve the tracking at high frequencies. A robust stability analysis and an analysis of the finite time convergence properties of the proposed controller are also provided in this paper. Simulation testing and an experimental validation using a linear actuator system with nonlinear friction and parameter uncertainties are conducted to verify the effectiveness of the proposed controller.     

线性电机伺服系统的自适应鲁棒控制

通过对一类音圈电机直驱式精密伺服系统运动控制问题的研究,在只考虑系统标称模型的情况下,采用分数阶形式的趋近律,得到了一种有限时间滑模控制算法;与此同时,当系统存在参数不确定和外界干扰的情况下,将有限时间滑模控制方法和自适应控制理论相结合,构造了一种自适应滑模控制律.另一方面,本文还考虑了系统具有输入饱和约束的情况,通过引入一个辅助系统,进而设计了一种自适应抗饱和控制律.而且,文中对闭环系统的稳定性进行了证明.最后,仿真和实验对所提出控制策略的有效性和伺服精度进行了对比、分析和验证.     

Integrated interceptor guidance and control with prescribed performance

Robustness and transient performance are the key performance indexes of the integrated interceptor guidance and control. However, these two performances have not yet been guaranteed comprehensively before. In this paper, a robust integrated interceptor guidance and autopilot controller is presented with prescribed steady state and transient performances of interception. On the basis of the dynamic surface control technique, the robustness of the proposed controller is improved by signal compensation. By utilizing the prescribed performance control theory, the transformed system of original integrated guidance and control model is stabilized to guarantee the prescribed performance of interception. It is proven that the stability of the transformed system is obtained by the loose selection of controller parameters, and therefore, the system robustness has been improved. Simulation results are included to verify the effectiveness of the proposed approach. Copyright © 2014 John Wiley & Sons, Ltd.     

Nonlinear sliding mode control of an unmanned agricultural tractor in the presence of sliding and control saturation

The paper considers the problem of automatic path tracking by autonomous farming vehicles subject to wheel slips, which are characteristic for agricultural applications. Two guidance laws are proposed to solve this problem, and both explicitly take into account the constraints on the steering angle and ensure tracking an arbitrarily curved path. The first law is implemented by the pure sliding-mode controller, whereas the second one combines the sliding mode approach with a smooth nonlinear control law and requests control chattering at the reduced amplitude as compared with the first law. Mathematically rigorous proofs of global convergence and robust stability of the proposed guidance laws are presented. In doing so, the slipping effects are treated as bounded uncertainties. Simulation results and real world experiments confirm the applicability and performance of the proposed guidance approach.     

Quasi sliding mode‐based single input fuzzy self‐tuning decoupled fuzzy PI control for robot manipulators with uncertainty

This paper presents a robust adaptive control strategy for robot manipulators, based on the coupling of the fuzzy logic control with the so‐called sliding mode control (SMC) approach. The motivation for using SMC in robotics mainly relies on its appreciable features. However, the drawbacks of the conventional SMC, such as chattering effect and required a priori knowledge of the bounds of uncertainties can be destructive. In this paper, these problems are suitably circumvented by adopting a reduced rule base single input fuzzy self tuning decoupled fuzzy proportional integral sliding mode control approach. In this new approach a decoupled fuzzy proportional integral control is used and a reduced rule base single input fuzzy self‐tuning controller as a supervisory fuzzy system is added to adaptively tune the output control gain of the decoupled fuzzy proportional integral control. Moreover, it is proved that the fuzzy control surface of the single‐input fuzzy rule base is very close to the input/output relation of a straight line. Therefore, a varying output gain decoupled fuzzy proportional integral sliding mode control approach using an approximate line equation is then proposed. The stability of the system is guaranteed in the sense of the Lyapunov theorem. Simulations using the dynamic model of a 3DOF planar manipulator with uncertainties show the effectiveness of the approach in high speed trajectory tracking problems. The simulation results that are compared with the results of conventional SMC indicate that the control performance of the robot system is satisfactory and the proposed approach can achieve favorable tracking performance, and it is robust with regard to uncertainties and disturbances. Copyright © 2011 John Wiley & Sons, Ltd.