zhangjie

关于心电图入门的基本知识，便于初学者学习和使用。(Getting Started on the basic knowledge of ECG, easy for beginners to learn and use.)

三阶锁相环频率合成器的simulink 模型，可以演示三阶锁相环工程过程，验证参数合理性(Three phase lock loop )

matlab程序，对图像做选取3*3矩阵的8邻域与中心特征值的像素差，然后按照不同的方式滑动(matlab program, the selected pixels of the image to make the neighborhood and the center differential 8 eigenvalues ​ ​ 3* 3 matrix, and then slide in different ways)

developing envelope matlab prog

该代码主要用于求最短路问题，开发环境为Matlab(The code is mainly used for the shortest path problem, the development environment for Matlab)

潮流计算是电力学名词，指在给定电力系统网络拓扑、元件参数和发电、负荷参量条件下，计算有功功率、无功功率及电压在电力网中的分布。潮流计算是根据给定的电网结构、参数和发电机、负荷等元件的运行条件，确定电力系统各部分稳态运行状态参数的计算。通常给定的运行条件有系统中各电源和负荷点的功率、枢纽点电压、平衡点的电压和相位角。待求的运行状态参量包括电网各母线节点的电压幅值和相角，以及各支路的功率分布、网络的功率损耗等。(Power flow calculation is a term of power science. It refers to the calculation of the distribution of active power, reactive power and voltage in power network under given network topology, component parameters and generation and load parameters. Power flow calculation is based on the given grid structure, parameters and operation conditions of generator, load and other components to determine the steady-state operation parameters of each part of the power system. Usually, the given operating conditions include the power of each power source and load point, junction voltage, balance point voltage and phase angle. The parameters to be determined include the voltage amplitude and phase angle of each bus node, the power distribution of each branch and the power loss of the network.)

S_函数使用及应用举例，本书详细的介绍了关于matlab中simulink仿真的基础知识(simulink S-function example)

AT88 PROGRAMMER DIAGRAM

精密控制结构需要满足先进飞机的使命和对其引航的要求。这就要求飞行器的性能必须满足在低空飞行，低速飞行和大迎角攻击性飞行，全天候，昼夜工作的条件，并且新的控制技术应该成熟。这项工作提出了飞行控制时，状态变量和控制输入是由预先确定的限制范围内的系统控制系统的设计理念。在设计过程使用动态规划的概念。其基本思想涉及非二次泛函最小化。由于一系列限制因素，建议使用光滑函数。同时提出了该综合方法的优点。我们利用对F-18战斗机的纵向控制配置来说明该设计方法。(Indirect adaptive control for reconfigurable flight control is advocated. Specifically, online static system identification using a moving window/batch estimation is implemented. The ensuing linear regression is augmented with an intercept. The intercept parameter is included to address the effects of trim change associated with the occurrence of a control surface failure. Parameter estimate information is used to adjust the inner loop’s control gains, and a command derived from the intercept estimate is fed forward to automatically retrim the aircraft. The tracking performance of this automatic retrimming method, which relies on system identification, surpasses the conventional approach of exclusively relying on integral action for retrimming. These adaptive and reconfigurable flight control concepts are illustrated in the context of a fighter aircraft’s pitch plane dynamics. The novel adaptive and reconfigurable flight control system successfully handles a 50 per cent horiz)

Partial Autocorrelation Function - Matlab - Useful Econometrics Tool