无人机光电载荷图像处理器的设计

介绍了无人机载设备的技术特点及机载小型图像处理器的组成。采用TI公司的数字信号处理器芯片为核心处理器,配合现场可编程逻辑器件(FPGA)与外部管理微控制单元(MCU)来实现目标数据的采集与处理,设计了适用于无人机光电载荷的超小型图像处理器系统。针对机载设备的特点,设计时充分考虑了体积、重量、功耗等要求。该系统已应用于多台套机载光电载荷中,工作稳定可靠,满足无人侦察机对捕捉和定位目标的要求。     

Finite-time disturbance observer-based trajectory tracking control for quadrotor unmanned aerial vehicle with obstacle avoidance

This paper investigates the problem of trajectory tracking control for quadrotor unmanned aerial vehicle (UAV) in the presence of dynamic obstacles and external disturbance forces/torques. More specifically, two new sliding mode disturbance observers are firstly designed to estimate the external disturbances, in which the observation errors can converge to zero in finite time. Furthermore, utilizing the observation information, a new sliding mode surface-like variable-based position tracking control scheme and a novel nonsingular terminal sliding mode-based attitude synchronization control scheme are developed to drive the UAV tracking the reference trajectory with obstacle avoiding. Moreover, the tracking errors of the close-loop control system can converge to zero within finite time by the analyses of Lyapunov methodology. Finally, the numerical simulation results are presented to illustrate the effectiveness of the proposed control schemes.     

两栖UAV滑跳动力学特性仿真研究

基于空气动力学、势流理论和二元平面滑行理论,建立了两栖UAV入水滑跳动力学模型,重点对两栖UAV入水滑跳动力学特性进行了分析,并研究了多种入水条件对滑跳状态的影响.结果显示:(1)两栖UAV触水瞬间,姿态出现明显变化,UAV出现瞬时剧烈抬头趋势;(2)两栖UAV入水攻角增大,会造成UAV较大的沾湿深度和较短的滑水时间;...     

基于CMOS图像传感器的微型无人机遥感系统设计

为了实现微小型无人机航空遥感,设计了一种基于CMOS图像传感器的微小型无人机的可见光遥感系统.系统采用CMOS图像传感器替代CCD,利用时序发生模块(Field-Prog Rammble Array,FPRA)实现了控制时序、数据缓存和硬件彩色插值,C8051F单片机作为主控核心,采用FLASH作为数据存储单元,设计了PAL制视频信号生成电路.介绍了所用CMOS图像传感器的特性,分析了Bayer颜色格式进行彩色插值恢复标准RGB颜色格式的硬件实现与软件算法.整个系统重量约20 g,功耗约2 W.在一款翼展800 mm的无人机上实现了遥感拍照,给出了处理后的拍照结果.     

无人机光电侦察设备控制系统设计研究

本文论述了某型无人机光电侦察设备控制系统设计和实现方法,通过对系统的主要技术指标进行分析,确定了技术方案,介绍及讨论了系统技术难点.同时介绍了系统的实现过程并对实现中遇到的问题进行了讨论.     

水稻分蘖期无人机高光谱影像混合像元特征分析与分解

开展水稻无人机高光谱解混,获取水稻植株的高光谱反射率信息,对于提高水稻理化参量的反演模型精度具有重要意义.目前大多基于高光谱遥感影像自身数据进行解混,运用算法模型进行高光谱数据解混,将高光谱图像和可见光图像进行优势互补,提出一种基于无人机高清影像与高光谱遥感影像融合的稻田无人机高光谱解混方法,解决单一数据局限性问题,增...     

基于几何矩预分类的无人机遥感图像自动配准方法

图像配准技术是近些年来图像处理领域发展迅速的研究方向之一.在遥感领域内,图像配准更是实现图像融合、运动检测、图像校正、图像拼接等应用的一个关键步骤.尽管国内外目前在图像配准方面提出了很多方法,但不同方法适用的图像范围不同,很多时候需要人工干预进行方法的选择.尤其对于无人机这种快速、实时获取图像的新型遥感平台,如何集合不同方法的优点以实现图像自动配准成为了关键性问题.本文在比较分析了基于SIFT和SURF特征提取图像配准方法的各自优势后,提出基于几何矩的方法对图像进行预先分类,从而决定将其分配给何种方法进行配准,实现全程自动化.实验证明,这种图像自动配准方法在拓宽了图像应用范围的同时保证了良好的配准效果.     

四旋翼无人机可视化轨迹跟踪仿真系统

为了便于对四旋翼无人机控制算法进行实验仿真和验证,联合Solidworks和Matlab/SimMechanics工具箱设计了一种四旋翼无人机可视化轨迹跟踪仿真系统;利用Solidworks搭建了四旋翼无人机三维实体模型,并通过Solidworks和Matlab转换接口将该实体模型导入到Matlab/SimMechanics中;Matlab/SimMechanics提供了了三维可视化窗口,可以显示无人机的实时仿真状态;仿真平台在Matlab/SimMechanics环境中实现,与Matlab/Simulink通信方便,可方便的将Simulink设计好的控制算法添加到仿真系统中,以进行验证和参数整定,还具有姿态分析和数据分析等功能;轨迹跟踪仿真结果表明,四旋翼无人机可视化轨迹跟踪仿真系统直观可视,准确可靠,能较好地对控制算法进行研究和测试,对四旋翼无人机以及控制算法的研究和开发具有重要价值。     

基于LabVIEW Vision的无人机自主着降系统设计与实现

四旋翼无人机具有低成本、垂直起降、机动性好等优点,在民用领域诸如航拍、植保、物流、电力巡线等场合得到了广泛的关注和应用。随着四旋翼无人机应用的普及,一些新的问题也随之出现,其中一个厄待解决的问题是如何提高无人机的降落精度和可靠性,特别在超视距应用场景下,这一需求尤为突出。通过采用机器视觉技术,利用LabVIEW Vision编制视觉识别软件,可以控制四旋翼无人机实现高精度的自主降落。     

Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation

Plasma flow control(PFC) is a new kind of active flow control technology, which can improve the aerodynamic performances of aircrafts remarkably. The flow separation control of an unmanned air vehicle(UAV) by nanosecond discharge plasma aerodynamic actuation(NDPAA) is investigated experimentally in this paper. Experimental results show that the applied voltages for both the nanosecond discharge and the millisecond discharge are nearly the same, but the current for nanosecond discharge(30 A) is much bigger than that for millisecond discharge(0.1 A). The flow field induced by the NDPAA is similar to a shock wave upward, and has a maximal velocity of less than 0.5 m/s. Fast heating effect for nanosecond discharge induces shock waves in the quiescent air. The lasting time of the shock waves is about 80 μs and its spread velocity is nearly 380 m/s. By using the NDPAA, the flow separation on the suction side of the UAV can be totally suppressed and the critical stall angle of attack increases from 20° to 27° with a maximal lift coefficient increment of 11.24%. The flow separation can be suppressed when the discharge voltage is larger than the threshold value, and the optimum operation frequency for the NDPAA is the one which makes the Strouhal number equal one. The NDPAA is more effective than the millisecond discharge plasma aerodynamic actuation(MDPAA) in boundary layer flow control. The main mechanism for nanosecond discharge is shock effect. Shock effect is more effective in flow control than momentum effect in high speed flow control.