shiyanwu

this is a [ortion of machine drive designind code.

说明：  可以很好的结合现有的信号数据进行分析和处理，得到一定优化效果(Can be a good combination of existing data analysis and signal processing, to a certain optimal results)

一个Rayleigh衰落的clarke模型的问题,主要是信道仿真方面的,实用.(a Rayleigh fading clarke model that the main problem is the channel simulation aspects. practical.)

1.OFDM入门零基础，及其宝贵和重要的仿真建模文档。 2.通过实例将OFDM在通信系统中的各种特性描述出来。 3.文档中含有该场景下所有仿真的源代码(文档的附录最后面)，已在matlab下全部编译通过。(1.OFDM entry zero-based, and its valuable and important documents simulation modeling. 2. By example in the OFDM communication system describe the various features. 3. A document that contains all the simulation under this scenario the source code (appendix to the final surface of the document), has been under the full compile matlab.)

说明：  该程序用于大地反算，参考于武汉大学测绘学院出版的大地测量学基础（第二版）(The inverse procedure for the earth, the reference in the School of Surveying and Mapping, Wuhan University, published the basis of Geodesy (second edition))

manuevering vessel models

编程实现以NRW算法通过S参数提取超材料结构的等效介电常数和等效磁导率(Programming in NRW algorithm to extract the effective permittivity and effective permeability metamaterial structure is obtained by S parameter)

说明：  混沌时间序列预测程序,包括多步预测函数及多步预报的主程序。(Chaotic time series prediction procedures, including multi-step prediction function and multi-step prediction of the main program.)

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)

stanford大学开发用于解优化问题的系统模型，可用于解压缩感知恢复算法：BP、DS等(the system modeldeveloped by stanford University is used for the solution of optimization problems, such as compressive sensing recovery algorithm: BP, DS)