微型仿昆飞行机器入驻飞时姿态控制的研究

对于微型仿昆飞行机器人驻飞时姿态的控制,提出了一个基于平均力矩的控制方案,并且通过改变翅的迎角来获得所需的姿态控制平均力矩.在每个拍动周期结束后,根据状态反馈误差调整迎角.在假设驻飞时姿态偏离角度较小的情况下,对控制系统进行了线性化近似和解耦.最后对控制系统进行了仿真,仿真结果表明了该系统具有鲁棒性.     

Robust Model-Free Control Applied to a Quadrotor UAV

The objective of this paper is to deal with a new technique based on Model-Free Control (MFC). The concept of this controller is to use a basic controller along with an ultra-local model to compensate for system’s uncertainties and disturbances. In this paper, a proposed algorithm is introduced based on an integrated structure between the Nonlinear Integral-Backstepping technique (NIB) and the MFC. The LQR, NIB, LQR-MFC, and NIB-MFC are implemented on a real quadrotor UAV. Various real-time flight tests are conducted to validate the importance of using the MFC side by side with NIB. The proposed combination shows robust performance compared to the other algorithms under fault-free and actuator fault conditions.     

Time-Optimal Control of a Hovering Quad-Rotor Helicopter

The time-optimal control problem of a hovering quad-rotor helicopter is addressed in this paper. Instead of utilizing the Pontryagin's Minimum Principle (PMP), in which one needs to solve a set of highly nonlinear differential equations, a nonlinear programming (NLP) method is proposed. In this novel method, the count of control steps is fixed initially and the sampling period is treated as a variable in the optimization process. The optimization object is to minimize the sampling period such that it will be below a specific minimum value, which is set in advance considering the accuracy of discretization. To generate initial feasible solutions of the formulated NLP problem, genetic algorithms (GAs) are adopted. With the proposed method, one can find a time-optimal movement of the helicopter between two configurations. To show the feasibility of the proposed method, simulation results are included for illustration.     

轴向主动磁轴承的无模型控制

轴向主动磁轴承系统是一个典型的非线性开环不稳定系统,且其准确模型也难以得到.它的控制一般是采用PID,但存在PID参数调整费时和扰动抑制效果差的问题.新的无模型控制方法不需要知道被控对象的精确模型和阶次.依据此方法所设计的控制器具有结构简单、控制参数调整方便等优点.因此,尝试将该新型控制方法应用于轴向主动磁轴承的控制.仿真和实验结果表明:与PID控制方法相比,应用该方法所设计的控制系统具有无超调、稳态精度高、对扰动抑制作用强等优点.     

基于电磁微马达的移动微机器人驱动控制

介绍一种基于MEMS技术制作的电磁微马达驱动的毫米级移动微机器人及其控制方案。该微型机器人体积为 9.5mm× 9.5mm× 9.5mm ,共有 3个微马达 ,两个用于轮子驱动 ,另外一个通过 3∶1的减速装置来控制微机器人全方位转动。微马达的直径只有 5mm ,是由微细加工工艺制作的。文中设计了一种新颖的控制电路 ,其核心使用微控制器 (MCU)AT90S85 15 ,通过键盘可以实现微机器人前进、后退、左转、右转和加速、减速 6种动作 ,并介绍了微马达的驱动控制方法和程序设计     

微扑翼飞行器控制系统相关技术研究进展

微型扑翼飞行器(FMAV)由于微型化和采用扑翼飞行方式的特征,许多传统理论和设计方法不再完全适用,相关理论和技术仍在不断地发展中,所以对国内外相关理论和技术的发展现状进行及时跟踪和研究,具有非常重要的参考意义;通过调查研究,介绍了与微型扑翼飞行器控制系统有关的低雷诺数非定常空气动力学、控制系统数学模型、控制方案和控制方法等的研究进展,总结出了微型扑翼对飞行器控制系统的设计要求,控制系统的特点和需要解决的关键问题,并展望了未来发展趋势。     

单输入单输出系统的模糊无模型自适应控制方法

根据无模型自适应技术的特点,提出了一种模糊无模型自适应控制方法.并对该方法的特点进行了分析.仿真结果表明,该方法原理简单、控制效果好,可应用于各种单输入单输出控制系统.     

基于模糊控制理论的无模型自适应控制技术

美国通控集团公司于 1 998年 1月推出了基于无模型自适应 (MFA)控制技术的产品 ,但却小心保护着MFA控制技术这一机密。本文根据美国通控集团公司的介绍 ,提出了MFA控制器的特点 ,并用模糊控制理论对单输入单输出 (SISO)系统和多输入多输出 (MIMO)系统的MFA控制技术进行了探讨     

一类离散时间非线性系统不依赖受控系统数学模型的学习自适应控制

给出了一类离散时间非线性系统的不依赖受控系统数学模型的学习自适应控制方案，它不需要受控系统的结构信息、数学模型、外部试验信号和训练过程，仅用受控系统的Ｉ／Ｏ数据来设计，传统的未建模动态不存在，所给出的计算机仿真结果说明了所给出的方案的正确性和有效性。     

一类离散时间非线性系统不依赖受控系统数学模型的学习自适应控制

给出了一类离散时间非线性系统的不依赖受控系统数学模型的学习自适应控制方案，它不需要受控系统的结构信息、数学模型、外部试验信号和训练过程，仅用受控系统的I／O数据来设计，传统的未建模动态不存在，所给出的计算机仿真结果说明了所给出的方案的正确性和有效性。     

Policy Gradient Adaptive Dynamic Programming for Model-Free Multi-Objective Optimal Control

<正>Dear Editor,In this letter, the multi-objective optimal control problem of nonlinear discrete-time systems is investigated. A data-driven policy gradient algorithm is proposed in which the action-state value function is used to evaluate the policy. In the policy improvement process, the policy gradient based method is employed,     

Low-Cost Visual Tracking of a Landing Place and Hovering Flight Control with a Microcontroller

The growth of civil and military use has recently promoted the development of unmanned miniature aerial vehicles dedicated to surveillance tasks. These flying vehicles are often capable of carrying only a few dozen grammes of payload. To achieve autonomy for this kind of aircraft novel sensors are required, which need to cope with strictly limited onboard processing power. One of the key aspects in autonomous behaviour is target tracking. Our visual tracking approach differs from other methods by not using expensive cameras but a Wii remote camera, i.e. commodity consumer hardware. The system works without stationary sensors and all processing is done with an onboard microcontroller. The only assumptions are a good roll and pitch attitude estimation, provided by an inertial measurement unit and a stationary pattern of four infrared spots on the target or the landing spot. This paper details experiments for hovering above a landing place, but tracking a slowly moving target is also possible.     

Modeling and Trajectory Tracking Control for Flapping-Wing Micro Aerial Vehicles

This paper studies the trajectory tracking problem of flapping-wing micro aerial vehicles(FWMAVs)in the longitudinal plane.First of all,the kinematics and dynamics of the FWMAV are established,wherein the aerodynamic force and torque generated by flapping wings and the tail wing are explicitly formulated with respect to the flapping frequency of the wings and the degree of tail wing inclination.To achieve autonomous tracking,an adaptive control scheme is proposed under the hierarchical framework.Specifically,a bounded position controller with hyperbolic tangent functions is designed to produce the desired aerodynamic force,and a pitch command is extracted from the designed position controller.Next,an adaptive attitude controller is designed to track the extracted pitch command,where a radial basis function neural network is introduced to approximate the unknown aerodynamic perturbation torque.Finally,the flapping frequency of the wings and the degree of tail wing inclination are calculated from the designed position and attitude controllers,respectively.In terms of Lyapunov's direct method,it is shown that the tracking errors are bounded and ultimately converge to a small neighborhood around the origin.Simulations are carried out to verify the effectiveness of the proposed control scheme.     

基于LQR的直升机悬停控制律设计与仿真

建立了某型直升机数学模型,并将该模型分解为纵向模型和横侧向模型两部分,提出了悬停控制律应该达到的稳态指标;以该型直升机为被控对象,采用输出反馈线性二次型调节器(LQR)技术设计了由纵向控制律和横侧向控制律组成的悬停控制律,使得直升机能取得满意的悬停性能指标;以该型直升机模型、执行器模型以及设计的悬停控制器构成全数字闭环仿真系统进行控制律仿真验证;仿真结果表明,文中设计的悬停控制律正确有效,能够较好地实现直升机的悬停功能,另外,由于该悬停控制律是基于输出反馈的,在工程上也比较容易实现。     

Safety-Critical Model-Free Control for Multi-Target Tracking of USVs with Collision Avoidance

<正>Dear editor, This letter addresses the multi-target tracking of underactuated unmanned surface vehicles(USVs) subject to multiple stationary/moving obstacles. The kinetic model parameters of each USV are totally unknown. A safety-critical model-free control method is proposed for tracking multiple targets with a collision-free containment formation.Specifically,     

双旋翼尾坐式飞行器建模及悬停姿态控制

基于双旋翼尾坐式飞行器的飞行原理,建立了其动力学模型,并对模型参数进行了整定。而后对其悬停模式下的姿态自稳定性进行了分析,并设计控制器对系统进行了校正。通过仿真和实验,验证了所设计的控制器具有较强的稳定性和鲁棒性。     

净水厂混凝投药的无模型自适应控制系统

针对净水工艺中混凝投药自动控制存在的问题,以沉淀池出口浊度为被控对象,絮凝剂投加量为调节手段,与加药流量子回路构成串级控制系统,采用无模型自适应(MFA)控制技术设计了混凝投药自动控制系统,给出了具体实施步骤.该系统利用抗滞后MFA控制器克服由于工艺原因造成的浊度闭环控制中的大滞后、大惯性和扰动问题,成功地解决了长期困扰净水行业的难题.上海某水厂的成功应用表明,该解决方案结构合理,投资省,效果好,工程量小,操作维护非常简单,为该问题的解决提供了一条很好的途径.     

Model-Free Optimal Consensus Control for Multi-agent Systems Based on DHP Algorithm

Neural Processing Letters - This paper developes a novel model-free dual heuristic dynamic programming (DHP) algorithm combined with policy iteration and least square techniques to implement...     

直升机自动过渡悬停控制系统设计

针对近海飞行的直升机高度测量信号中海浪噪声的干扰,利用有理谱法建立了海浪模型,设计了卡尔曼滤波器估计噪声信号,以获取精确的高度信号;根据自动过渡模态的基本要求,开发设计了反潜直升机自动过渡悬停的飞行控制系统;通过引入速度比较器和限幅器,保证当直升机高度接近悬停高度时,地速同步趋近于零,实现了高度和速度两通道之间协调控制,使直升机平滑过渡至悬停状态;对工程应用中可能出现的特殊情况及相应的处理方法进行了分析;仿真结果表明,设计的仿真系统能很好的反应真实情况,控制结构具有良好的抗风干扰能力和鲁棒性,参数摄动10%以及海浪加剧时仍保证直升机按预期轨迹运动,工程应用性强。