共查询到18条相似文献,搜索用时 136 毫秒
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应用精确线性化方法研究了永磁同步电动机的非线性控制问题.根据精确线性化理论,设计了永磁同步电动机状态反馈线性化控制器和相对阶为1的多指标输入输出反馈线性化控制器.多指标非线性控制器选择全状态量线性组合形式为输出函数,根据系统特征根配置方法,整定了输出函数中各状态量的反馈系数.比较2种控制器仿真结果发现,多指标非线性控制器可以实现对电动机转速的有效控制,且控制器结构简单,设计方便,动静态性能良好. 相似文献
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抑制飞控系统极限环的非线性方法 总被引:1,自引:0,他引:1
抑制飞控系统极限环振荡是设计数字电传系统时需要解决的重要问题。针对飞控系统中常见的不确定非线性,提出仿线性元件的思想,以实现所期望的系统稳定裕度,从而克服非线性所造成的影响;针对确定的非线性,提出了非时变非线性可补性的概念,并应用于控制器中,实现非线性的补偿。将两种方案用于飞控系统中,仿真结果表明,对抑制系统的极限环是有效的。 相似文献
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一类非线性系统的变结构控制问题 总被引:1,自引:0,他引:1
本文研究了简约型非线性控制系统的变结构控制问题,针对变结构控制切换函数的确定问题进行了深入研究,给出了一类非线性系统切换函数的确定方法。研究结果表明,该方法适用于一类难于或不能可控正则化和线性化的非线性控制系统的综合。最后通过仿真证实了该方法的有效性。 相似文献
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The application of artificial neural networks for aircraft motion control, in particular, for creation of nonlinear algorithms of the aircraft remote control system (RCS) is considered. Aircraft as a control object is represented as a multidimensional nonlinear dynamic system and nonlinear control methods are used to operate this system. The control loop is constructed using the method of inverse dynamics based on the feedback linearization principle. The nonlinear control law is represented as a neural network being learned (adjusted) by recorded or incoming measurements of motion parameters. Synthesis and testing of neural network control algorithms is performed with the fully nonlinear mathematical model of a maneuverable aircraft for three control channels. Simulation results of the closed system are presented. 相似文献
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采用非线性系统扩展线性化方法设计飞控系统 总被引:2,自引:0,他引:2
利用非线性系统的扩展线性化方法设计具有大迎角的非线性飞行控制系统。在系统的静态平衡点族上进行线化及调节器设计并直接积分得到非线性控制律,同时利用等效系统法验证飞行品质。整个设计过程较简便,控制律便于实现,飞机的失速迎角有较大提高,飞行品质也是令人满意的。 相似文献
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基于BACKSTEPPING理论的直接自适应飞行控制 总被引:2,自引:0,他引:2
BACKSTEPPING理论是继反馈线性化理论之后发展起来的一种的控制理论.基于BACKSTEPPING理论的控制系统是通过Lyapunov稳定性理论推导得出,确保了系统闭环稳定性,避免了反馈线性化理论在飞机控制系统中应用存在的可能不稳定的隐患.然而,BACKSTEPPING理论与反馈线性化方法存在同样的鲁棒性缺陷,即对模型的精确性要求很严格.据此文中给出一种通过直接自适应补偿的方式来增强其鲁棒性的方法.仿真结果表明此方案对模型存在不精确环节时有较强的补偿控制作用. 相似文献
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The mathematical model of a transport aircraft would be subjected to a sudden change when heavy cargo is dropped off in airdropping, which exerts serious influences upon the safety of the aircraft. A variable structure controller is specially designed for handling the airdrop process. The nonlinear system is linearized by input-output feedback linearization using differential geometry theories. On this basis, an inner loop system for velocity and attitude tracking control is designed by using the exponentially approaching rule of the variable structure theory. The whole flight control system is integrated with the outer loop flight altitude control. Digital simulation evidences the applicability of the system to potentially catastrophic course in airdropping heavy cargo and provides robustness against system parameter perturbation. 相似文献
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提出了一种基于神经元网络的飞行控制系统设计方法 ,该方法设计的神经元飞行控制器具有良好的鲁棒性 ,使飞行器在整个飞行包络内都能保持某种最优的操纵品质。给出的计算机仿真结果显示出神经元网络作为飞行控制器在处理飞行器参数大范围变化的非线性特性方面具有潜在的优良品质 相似文献
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《IEEE transactions on aerospace and electronic systems》2006,42(3):825-845
The problem of automated attitude recovery of rigid and flexible spacecraft is investigated using feedback linearization control and a novel approach for generating the control error signal based on quaternion addition. The attitude and flexible dynamics equations for a class of spacecraft is presented. The resulting nonlinear and coupled equations of the system are implemented into a high-fidelity user-friendly simulation environment. The simulator is used for the investigation of attitude recovery of flexible spacecraft using the feedback linearization approach. Since the flexible spacecraft is underactuated, the input-output linearization technique was specifically used to break up the system into two distinct parts, namely 1) an external linearizable system for which a linear controller can be easily implemented, and 2) an internal nonlinear unobservable system for which the associated zero dynamics is shown to be asymptotically stable for two representative cases. The overall closed-loop stability of the flexible spacecraft is analyzed rigorously and shown to be asymptotically stable using Lyapunov's method 相似文献
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针对飞机控制系统执行机构具有非线性这一特点,选用某歼击机作为研究对象,分析各类非线性环节对飞机纵向短周期特性的影响。首先分析了死区、间隙和速率饱和等非线性环节的基本特性,建立了相应的包含非线性环节的飞行动力学模型,然后,基于Chalk准则计算不同非线性参数下的飞行品质指标,进行飞行品质评价。通过对不同飞控系统构型的对比研究,探讨了执行机构非线性对飞行品质的影响。研究结果表明,各非线性环节都将对系统的快速性产生不利影响,使系统有效上升时间增加,相位延迟增加。其中,间隙还会造成系统阻尼减小,可导致系统不稳并出现极限环振荡。 相似文献
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In this paper, we consider different approaches for the neural network controller tuning in the flight control system. Two of the most common tuning approaches in the adaptive control theory are applied. The first one uses parameter identification technique and consists in solving a real-time regression problem for the control law. The second approach is based on the Lyapunov direct method, which utilizes a tracking error as an absolute measure of tuning performance. The neural network control law are designed for the three-axis flight control problem and tested on the full nonlinear model of a fighter aircraft. Closed loop simulation results are presented and two adaptation algorithms are compared in the case of abrupt change of aircraft dynamics. 相似文献