IMMPDA

说明：  这是一个机器人轨迹跟踪控制的程序，应用的控制算法为滑模控制。(This is a robot trajectory tracking control program, the application of the control algorithm for sliding mode control.)

通过python语言实现，利用遗传算法求解二元函数最大值(Using Python language and genetic algorithm to solve the maximum of binary function)

说明：  实现多种二维面阵的综合设计，包括均匀阵、切比雪夫阵等等。。。。(Comprehensive design of various 2D arrays)

基于ANSYS分析平台的铰接薄壳的后屈曲分析--APDL(Post-buckling analysis of articulated thin shells based on ANSYS analysis platform--APDL)

机械动力学进行模态分析，频响应分析等动力学的分析(Modal analysis, frequency response analysis and other dynamic analysis of mechanical dynamics.)

说明：  计算FDTD远场分析脚本，根据近场数据直接计算出远场分布(The far field analysis script of FDTD is calculated, and the far field distribution is calculated directly from the near field data.)

动网格，DEFINE_CG_MOTION，DEFINE_GRID_MOTION，很好的模板(dynamic mesh good template)

说明：  These composite materials generally exhibit brittle damage behavior. The anisotropy in the material and different kinds of failure mechanisms make it difficult to accurately characterize the behavior of composite materials. The present work aims to verify and apply the Puck Failure Criteria using the commercially available finite element package ANSYS by writing a user-material subroutine in FORTRAN. The model is implemented with different post failure degradation schemes EWM/CSE.

基于SAR-ADC的DAC模块的电容切换，所做的动态功耗仿真，比较了不同切换模式的功耗。(Capacitance switching of DAC module based on SAR-ADC is simulated and power consumption of different switching modes is compared.)

说明：  卫星姿态是指卫星星体在轨道上运行所处的空间指向状态。将直角坐标系的原点置于星体上，指向地面的Z轴反映偏航方向，Y轴反映俯仰方向，X轴反映滚动方向。星体在高空中沿局部地球铅垂方向和轨道矢量方向运行，不时地产生对三轴的偏移。姿态控制是通过姿态控制分系统（ACS）来实现，使用地平扫描仪可感应俯仰和滚动轴的姿态误差，使用速度陀螺仪和罗盘可感应偏航轴的姿态误差。(Satellite attitude refers to the spatial orientation of a satellite in orbit. The origin of the Cartesian coordinate system is placed on the star, the Z axis pointing to the ground reflects the yaw direction, the Y axis reflects the pitching direction, and the X axis reflects the rolling direction. The stars move along the direction of the earth's vertical direction and the orbit vector in the high altitude, resulting in the deviation of the three axis from time to time. Attitude control is realized by attitude control subsystem (ACS). The attitude error of pitch and rolling axis can be induced by using horizon scanner, and the attitude error of yaw axis can be induced by using speed gyroscope and compass.)