m32test

The example included here is a simple temperature conversion module that takes user-supplied temperature values specified in either degrees Fahrenheit or degrees Celsius and converts them to the other scale. The example demonstrates how to use the MATLAB® Builder™ JA API to handle temperatures in various different formats (scalars, matrices, cell arrays, and structs).

说明：  应用无迹卡尔曼滤波较好的实现单目标跟踪。(Unscented Kalman filter applied to achieve good single-target tracking.)

matlab gui设计,gui是matlab中比较常用一个方面，从不同的角度来分析设计(matlab programe please input in it)

单级倒立摆的PID控制 控制的目标是通过给小车底座施加一个力，使小车停留在预定的位置，并使杆不倒下 (lqr matlab)

OFDM LSE Channel Estimation； the performance of LSE channel estimation will be evaluated based on bit error rate in received data(OFDM Channel Estimation; performance of the channel estimation will LSE be evaluated based on bit error rate in received data)

对输入的语音信号运用短时能量函数进行去静音，然后把去掉静音帧之后的信号进行重组。(remove the mute of the speech signal (using short-term energy function), and then remove the signal mute frame after restructuring.)

Peak finding and measurement

区域生长算法，一种传统的图像分割算法，用于图像分割。(region growing algorithm for image segmentation .it is a trditional image segmentatin algorithm.)

FFT and IFFT 64 point radix-4

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)