共查询到20条相似文献,搜索用时 187 毫秒
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针对多变量、不稳定的近空间飞行器姿态系统,在系统存在参数不确定和外部干扰的情况下,并考虑执行器动态和输入受限,提出一种鲁棒可重构跟踪控制策略.首先,利用二阶滑模干扰观测器分别重构姿态、角速率回路的复合干扰;其次,采用鲁棒二阶滑模积分滤波器的反推(backstepping)方法避免了控制器设计中微分项膨胀问题,利用鲁棒项抵消重构误差对系统的影响,以实现姿态控制器设计.然后,在考虑执行器动态、输入受限及舵面卡死故障下,给出一种线性矩阵不等式的在线优化舵面分配算法,以实现飞行器的姿态角渐近跟踪期望的制导指令.最后,仿真结果表明所提出的方法具有良好的跟踪控制性能. 相似文献
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进行飞机翼面损伤下的重构控制对提高飞机的安全可靠性具有重要的意义,根据飞机翼面损伤的特点,提出一种基于L1自适应控制的重构控制方法,首先根据翼面故障对飞机气动特性的影响,建立故障参数模型,然后根据L1自适应控制快速自适应和鲁棒性的特点,选择合适的自适应律和滤波器进行重构控制器的设计,最后根据飞机升降舵翼面损伤情况进行仿真分析,结果表明了本文所用方法可以进行部分翼面损伤的快速重构控制。 相似文献
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本文采用比离散模型更一般的连续增益故障模型,提出了线性不确定系统考虑执行器故障鲁棒H∞可靠控制问题,利用 LMI分别给出了多故障鲁棒 H∞可靠控制器和单故障鲁棒 H∞可靠控制器存在的充分条件。在故障情况下,保证闭环系统渐近稳定和可接受的性能指标基础上,优化了无故障正常情况下的指标。在仿真实例中,不仅验证所提出方法的可行性,而且比较了鲁棒 H∞正常控制器和鲁棒 H∞可靠控制器的控制效果,进一步看出对系统进行最优鲁棒 H∞可靠控制器设计的必要性。 相似文献
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小型无人机一般采用单余度设计,舵面故障后重构控制只能根据系统解析冗余进行设计,传统辨识方法复杂而且往往不能满足无人机重构控制的实时性。对由于舵面故障多样性引起的无人机参数大范围跳变进行分析,采用基于线性模型的方法离线重构控制器参数,实际飞行中在线自适应选择控制律,并针对存在大扰动的重构过程设计了动态补偿方案,保证无人机在故障发生后重构完成前的过渡过程的安全性。仿真实验表明,该方法能满足无人机舵面故障时控制律重构的实时性要求,保证过渡过程平稳,而且基于线性模型的控制器设计方法简便,工程实用性强。 相似文献
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由降阶模型设计全阶模型的H~∞鲁棒控制器王炎生,陈宗基(北京航空航天大学自动控制系北京100083)关键词:模型降阶,H~∞鲁棒控制器,控制输入约束1引言近年来,具有良好鲁棒性的H”方法已经越来越多地应用于飞机控制系统设计研究中.但由于像飞机这样的被控... 相似文献
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采用比中断模型更一般的连续增益故障模型,提出线性系统考虑执行器故障的鲁棒H∞可靠控制问题。利用线性矩阵不等式LMI分别给出执行器故障鲁棒H∞控制器存在的充分条件。在保证闭环系统故障发生时的渐近稳定和可接受的性能指标基础上,优化了无故障情况下的性能指标。仿真数例验证了所提出方法的可行性和对系统进行鲁棒H∞控制器设计的必要性。 相似文献
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This paper is concerned with the problem of smooth switching state feedback controller design for aircraft dynamic systems with multiple operating points. Based on the theory of robust control, a single state feedback controller which considers smooth switching is constructed. With the constant controller, the output response can be considerably improved in the switching process when the flight condition changes. An example for autopilot design of an F‐18 aircraft is given to illustrate the effectiveness of the proposed approach. 相似文献
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Gain-scheduled directional guidance controller design using a genetic algorithm for automatic precision landing 总被引:1,自引:0,他引:1
Cheolkeun Ha 《International Journal of Control, Automation and Systems》2010,8(1):107-117
This paper discusses the guidance controller design problem of an aircraft in automatic landing and touchdown flight, subject to dangerous and unpredictable gusts known as wind-shear and to directional crosswind. The associated airplane in the landing flight was statically unstable in this paper. The wind-shear, based on the Dryden gust model, was included in the nonlinear airplane model. A directional guidance control system with gain-scheduling fuzzy logic was proposed in this paper. In fuzzy logic, an even number of exponential membership functions in the output are considered and their shape, decay rate, and scaling factors are optimized using a genetic algorithm. In this control system, the glide slope capture logic and the flare logic were also included for longitudinal and lateral control, respectively. The nonlinear aircraft model simulation illustrated that the proposed guidance control system shows satisfactory performances in accurate touchdowns and is adequately robust to the strong crosswind and wind-shear turbulences. 相似文献
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针对现代民用飞机非线性和时变的特点,设计了一种用于民机自动油门控制系统的模糊PID控制器;模糊控制器以速度跟踪误差及其微分信号作为输入调节PID控制器的比例、积分及微分参数,进而控制油门开度以调节发动机推力,最终实现对速度的控制;文中进一步采用广义自适应遗传算法(GSAGA)对模糊PID控制器的输出因子进行优化,在着陆模态下采用所设计的优化控制策略与传统模糊PID控制进行了对比仿真,仿真结果显示,在民机自动油门控制系统中基于GSAGA的模糊PID控制器的控制效果优于传统模糊控制方法,仿真结果符合飞行品质指标,控制效果良好。 相似文献
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飞机在飞行时,外界气流总存在不确定的扰动,对飞机的性能甚至稳定性会产生消极的影响。以某型飞机作为研究对象,在建立了综合飞行/推进系统(纵向)小偏离线性化数学模型后,根据H∞鲁棒控制理论所推导出的线性矩阵不等式,设计出干扰情况下的状态反馈控制器。仿真结果表明,所设计出的鲁棒控制器能够到达控制要求,在存在较大干扰时有一定的抑制作用。对于(LMI)线性矩阵不等式的H∞鲁棒控制方法在设计综合飞行/推进鲁棒控制系统时,是可行的,且能较好的解决飞行时存在的扰动问题。 相似文献
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In this paper,a novel version of six-degree-of-freedom nonlinear model for transport aircraft motion in cargo extraction is developed and validated by the theoretical mechanics and flight mechanics.In this model constraint force and moment reflecting the flight dynamic effects of inner moving cargo are formulated.A methodology for a control law design in this phase is presented,which linearizes the aircraft dynamics making use of piecewise linearization and utilizes robust control technique for interval system to achieve specified handling qualities with robustness to uncertainties.The simulations demonstrate adequate effectiveness and excellent robustness of the proposed controller. 相似文献
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In this paper, we apply a so‐called robust and perfect tracking (RPT) control technique to the design and implementation of the flight control system of a miniature unmanned rotorcraft, named HeLion. To make the presented work self‐contained, we will first outline some background knowledge, including mainly the nonlinear flight dynamics model and the inner‐loop flight control system design. Next, the highlight of this paper, that is, the outer‐loop flight control system design procedure using RPT control technique, will be detailed. Generally speaking, RPT control technique aims to design a controller such that (i) the resulting closed‐loop system is asymptotically stable, and (ii) the controlled output almost perfectly tracks a given reference signal in the presence of any initial conditions and external disturbances. Since it makes use of all possible information including the system measurement output and the command reference signal together with all its derivatives (if available) for control, RPT control technique is particularly useful for the outer‐loop layer of an unmanned aircraft. Both simulation and flight‐test results will be presented and analyzed at the end of this paper, and the efficiency of the RPT control approach will be evaluated comprehensively. 相似文献
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A.A. El-Mahallawy H.A. Yousef M.I. El-Singaby A.A. Madkour A.M. Youssef 《Expert systems with applications》2011,38(1):169-174
A proposed approach to robust controller design is introduced. This approach combines the recessive trait crossover genetic algorithm with the loop-shaping design procedure using H∞ synthesis. The requirements, design and simulation of a flight control system for precision tracking task are considered. The proposed method is applied to design a control system for the F-16 fighter aircraft model. The flight simulations reveal that the desired performance objectives are achieved and that the controller provides acceptable performance in spite of modeling errors and plant parameter variations. 相似文献
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The loss of measurements used for controller scheduling or envelope protection in modern flight control systems due to sensor failures leads to a challenging fault‐tolerant control law design problem. In this article, an approach to design such a robust fault‐tolerant control system, including full envelope protections using multiobjective optimization techniques, is proposed. The generic controller design and controller verification problems are derived and solved using novel multiobjective hybrid genetic optimization algorithms. These algorithms combine the multiobjective genetic search strategy with local, single‐objective optimization to improve convergence speed. The proposed strategies are applied to the design of a fault‐tolerant flight control system for a modern civil aircraft. The results of an industrial controller verification and validation campaign using an industrial benchmark simulator are reported. 相似文献