Role of Nd-Ni on structural,spectral and dielectric properties of strontium-barium based nano-sized X-type ferrites

The influence of neodymium and nickel substitution on structural and dielectric parameters was investigated in strontium-barium X-type hexagonal ferrites having composition SrBaCu_2?xNi_xNd_yFe_28?yO₄₆ (x = 0, 0.2, 0.4, 0.6, 0.8, 1 and y = 0, 0.02, 0.04, 0.06, 0.08, 0.1). Sol-gel method was employed for synthesizing these hexagonal ferrites. The XRD plots of all studied materials which were annealed at 1250 °C show single phase characteristics. Lattice parameter ‘c’ increased as a consequence of larger radius of rare earth ion (Nd³⁺) as compared to (Fe³⁺), while lattice parameter ‘a’ showed very small variation. The cell volume was obtained in the range 2508.32–2523.75 (ų). The inclusion of Nd-Ni also affected X-ray density, bulk density and porosity. The FTIR spectroscopy indicated the particular absorption peaks of hexagonal ferrites and it was performed in the range of 500–700 cm^?1. On account of Nd-Ni doping, the dielectric constant, dielectric loss and AC-conductivity showed decreasing trend. The occupancy of Nd³⁺ ions at octahedral site impedes the valence alternation of Fe³⁺; therefore there was decrease in dielectric permittivity. Ac conductivity has been decreased from 9.14 to 6.49 (Ω cm)^?1 at frequency of 2.7 GHz. The Cole-Cole plots of synthesized materials noticeably revealed grain boundary contribution. The appearance of single semi-circle in impedance Cole-Cole graphs confirms the exceptional role of grain boundaries in the conduction process. The considerably lower dielectric parameters of investigated nano X-type ferrites propose their feasibility for high-frequency applications (phase shifters, dielectric resonators, stealth technology etc).     

On Trajectory Tracking Model Predictive Control of an Unmanned Quadrotor Helicopter Subject to Aerodynamic Disturbances

In this article a model predictive control (MPC) strategy for the trajectory tracking of an unmanned quadrotor is presented. The quadrotor's dynamics are modeled using a hybrid systems approach and, specifically, a set of piecewise affine (PWA) systems around different operating points of the translational and rotational motions. The proposed control scheme is dual and consists of an integral MPC for the translational motions, followed by an MPC scheme for the tracking of the quadrotor's attitude motions. By the utilization of PWA representations, the controller is computed for a larger part of the quadrotor's flight envelope, which provides more control authority for aggressive maneuvering. The proposed dual control scheme is able to calculate optimal control actions with robustness against atmospheric disturbances (e.g. wind gusts) and with respect to the physical constraints of the quadrotor (e.g. maximum lifting forces or fixed thrust limitations in order to extend flight endurance). Extended simulation studies indicate the efficiency of the MPC scheme, both in trajectory tracking and aerodynamic disturbance attenuation.     

Ultralight X-type lattice sandwich structure (I): Concept,fabrication and experimental characterization

A new type of ultra-lightweight metallic lattice structure (named as the X-type structure) is reported. This periodic structure was formed by two groups of staggered struts in the traditional pyramid structure, and fabricated by folding expanded metal sheet along rows of offset nodes and then brazing the folded structure (as the core) with top and bottom facesheets to form sandwich panels. The out-of-plane compressive and shear properties of the X-type lattice sandwich structure were investigated experimentally and compared to those of the sandwich having a pyramidal truss core. It is found that the formation of the 2-dimensional staggered nodes can effectively make the X-type structure more resistant to inelastic and plastic buckling under both compression and shear loading than the pyramidal lattice truss. Obtained results show that the compressive and shear peak strengths of the X-type lattice structure are about 30% higher than those of the pyramidal lattice truss having the same relative density. Supported by the National Basic Research Program of China (“973” Project) (Grant No. 2006CB601202), the National Natural Science Foundation of China (Grant Nos. 10632060,10825210), the National “111” Project of China (Grant No. B06024) and the National High-Tech Research and Development Program of China (“863” Project) (Grant No. 2006AA03Z519)     

基于模型的四旋翼无人机半实物仿真平台研究

为了降低在真实飞行器上测试新的控制策略时所存在的设备损坏风险,对四旋翼无人机的控制器和半实物仿真实验平台进行了开发和介绍;首先,分析了四旋翼无人机基本结构和飞行原理,并对其进行了动力学建模;其次,设计了对应的常规PID控制器和滑模控制器,并进行了Matlab仿真对比和分析;最后,展示了采用先进的基于模型的设计方法和代码自动等技术的半实物仿真实验平台,并详细介绍了其硬件和软件的总体架构和不同模块的配置;仿真结果表明所设计滑模控制器相比于PID控制器有更好的控制效果,并给出了其在半实物仿真平台上用来研究四旋翼无人机姿态控制的可行性。     

基于强化学习的四旋翼无人机控制律设计

目前四旋翼无人机大部分都采用经典控制方法进行控制律的设计,然而控制参数的选择和对被控对象数学模型的依赖一直是经典控制方法设计中需要克服的问题;针对此问题,采用了一种基于深度强化学习算法Deep Q Network的无人机控制律设计方法,以四旋翼姿态角和姿态角速率作为三层神经网络的输入数据,最终输出动作值函数,再根据贪婪策略进行动作的选取,通过与环境的不断交互,智能体根据奖惩信息来更新神经网络的权值,使得智能体朝着获得累积回报最大值的方向选取动作;仿真结果表明在经过强化学习训练之后,四旋翼姿态角能够快速准确地跟踪上参考指令的变化,证明了基于强化学习的四旋翼无人机控制律的可行性,从而避免了传统控制方法对控制参数的选择与控制模型的依赖。     

基于终端滑模的四旋翼飞行器非线性轨迹跟踪控制

考虑到四旋翼飞行器的传统内外环控制策略依赖时标分离假设,稳定性分析复杂,并且控制参数选取困难的缺点,提出了一种与传统内外环控制策略不同的轨迹跟踪控制器;首先将四旋翼飞行器数学模型进行相应的变换,以分解为高度、偏航角和纵横向三个级联的子系统,再使用终端滑模控制方法设计高度和偏航角子系统的控制器,使两个子系统的状态误差可以在有限时间内收敛到原点,之后基于变量非线性变换设计纵横向子系统的控制器,分析了闭环系统稳定性,证明了所设计的轨迹跟踪控制器可以保证闭环系统跟踪误差渐近稳定到原点,最后仿真实验的结果验证了所设计的控制器的有效性。     

基于RFID技术的四旋翼无人机轨迹跟踪控制系统设计

为促进四旋翼无人机的飞行自主性,增强无人监管情况下飞行器主机所具备的避障行进能力,设计基于RFID技术的四旋翼无人机轨迹跟踪控制系统;采用RFID标签识别技术,调制处理既定控制信号,利用标签识别协议,连接微型四旋翼轨迹控制器与内环姿态控制器,通过数据通信链路,提取轨迹跟踪控制所需的传输电子量,完成轨迹跟踪控制系统硬件设计;利用动力系统中的参数辨识策略,确定与轨迹姿态控制相关的物理规律标注,实现四旋翼无人机轨迹跟踪控制;实验结果表明,与机器视觉型控制系统相比,基于RFID技术的控制系统的SSI避障行进指标数值相对较高,全局最大值达到了 79％,四旋翼无人机滚转角平均值为85°,能够有效抑制四旋翼无人机滚转角的数值上升趋势,增强无人监管情况下飞行器主机避障行进能力.     

四旋翼飞行器的自抗扰飞行控制方法

针对四旋翼飞行器参数不确定性和外部干扰敏感的问题,本文提出一种基于自抗扰控制器的控制系统设计方法.在为期望姿态和高度安排过渡过程的基础上,设计了扩张状态观测器对内扰和外扰进行估计并实时补偿,能够很好地克服飞行器的强耦合性、模型不确定性以及风速变化等外部干扰问题.此外本文还设计了非线性状态误差反馈控制律来有效抑制跟踪误差.在仿真平台上对自抗扰控制系统进行稳定控制、姿态跟踪、高度控制、抗扰性及鲁棒性实验,并与串级PID控制系统进行定量对比分析.仿真结果表明,本文所设计的自抗扰控制器不仅能够很好地估计并补偿系统所受内外部干扰,而且对四旋翼飞行器参数的不确定性具有较强的鲁棒性,能够满足飞行器姿态调节快速和高稳定度的控制要求,性能指标明显优于串级PID控制器.     

输入饱和与姿态受限的四旋翼无人机反步姿态控制

本文针对四旋翼无人机研究了鲁棒反步姿态控制策略.由于四旋翼无人机结构复杂,其非线性数学模型难以精确建立,因此在控制器设计过程中需要综合考虑模型不确定性、未知外部干扰、输入饱和以及姿态受限等因素.针对模型中的不确定项,使用神经网络进行逼近;对于外部未知干扰,使用非线性干扰观测器进行补偿;使用双曲正切函数逼近饱和函数,解决输入饱和问题;同时使用界限Lyapunov函数设计控制器,确保姿态满足限制条件.最后,设计四旋翼无人机反步姿态控制器,并根据Lyapunov稳定性定理证明了闭环控制系统的有界稳定.仿真结果表明了所研究控制方法的有效性.     

基于多传感器的四旋翼飞行器硬件系统设计

四旋翼飞行器由于其简单的机体结构与较为复杂的姿态控制,近年来在军用和民用领域广泛应用。旨在通过四旋翼飞行器飞控平台的搭建,实现对飞行器姿态的稳定控制。首先论述了四旋翼飞行器的飞行原理与机械结构,给出了硬件系统总体结构。在对各功能模块整合的基础上,实现基于多传感器的控制系统硬件电路设计。仿真与实验证明：多传感器使用过程中,通过卡尔曼滤波进行姿态数据的融合,有效地解决了加速度计、陀螺仪易受外界干扰问题,所设计硬件系统在飞行实验中性能稳定,为四旋翼的稳定控制提供了参考。