基于多模型半参数非线性回归模型的外弹道节省参数估计

双星定位系统的应用是外弹道估计中的一种发展趋势。文章给出基于双星、光雷的联合测量模型,建立基于半参数回归的外弹道节省参数估计模型;给出基于半参数回归的外弹道节省参数估计算法及计算步骤,并从理论上分析了基于半参数回归的外弹道节省参数估计算法能有效地消除非线性因素对参数估计性能的影响,其估计精度优于经典的节省参数建模方法,并通过仿真得到：该算法确实有效。     

某型电视制导空地导弹仿真研究

为了实现某型电视制导空地导弹全数字模拟,从而达到该型导弹经济、安全以及经常性训练的目的,根据该型导弹实际的工作原理和过程以及弹道性能参数,建立了该型导弹的弹道数学模型、碰撞检测模型和"人在回路"模型,实现了该型导弹对地攻击全过程仿真,补充了某型模拟器的战术模拟性能,有利于增强空军的空对地精确打击能力。     

An iterative linear quadratic regulator based trajectory tracking controller for wheeled mobile robot

We present an iterative linear quadratic regulator(ILQR) method for trajectory tracking control of a wheeled mobile robot system.The proposed scheme involves a kinematic model linearization technique,a global trajectory generation algorithm,and trajectory tracking controller design.A lattice planner,which searches over a 3D(x,y,θ) configuration space,is adopted to generate the global trajectory.The ILQR method is used to design a local trajectory tracking controller.The effectiveness of the proposed method is demonstrated in simulation and experiment with a significantly asymmetric differential drive robot.The performance of the local controller is analyzed and compared with that of the existing linear quadratic regulator(LQR) method.According to the experiments,the new controller improves the control sequences(v,ω) iteratively and produces slightly better results.Specifically,two trajectories,’S’ and ’8’ courses,are followed with sufficient accuracy using the proposed controller.     

基于非线性PID的柔性两轮机器人运动控制

柔性两轮机器人是一种不稳定、非线性、强耦合系统。该系统的突出特点是在机器人的腰部装有柔性的机体结构,能够更好地模拟人和动物的生物动力学特性,具有更好的仿生性质,同时,系统的控制难度显著增大,为使机器人能够平衡直立运动,且具有较强的鲁棒性,提出了非线性PD的姿态平衡控制方法,实现了机器人的姿态平衡,并同时设计了PID航向差动控制结构驱动左右轮电机,使机器人能够完成直线行进、自旋、环绕等多种运动平衡模式。实验结果表明,机器人具有优良的平衡能力和机动性能,从而验证了方法的有效性。     

Ultrasonic-assisted drilling of Inconel 738-LC

Generally in the drilling of modern aviation materials such as nickel and titanium base super alloys, problems frequently occur in terms of burr formation at the cutter exit, tool stress, high heat generation on tool surface as well as low process reliability. A recent and promising method to overcome these technological constraints is the use of ultrasonic assistance, where high-frequency and low-amplitude vibrations are superimposed on the movement of cutting tools. This paper presents the design of an ultrasonically vibrated tool holder and the experimental investigation of ultrasonically assisted drilling of Inconel 738-LC. The circularity, cylindricity, surface roughness and hole oversize of the ultrasonically and conventionally drilled workpieces were measured and compared. The obtained results show that the application of ultrasonic vibration can improve the hole quality considerably. Improvements of up to 60% have been achieved.     

步进电机S曲线精确控制的研究与验证

针对生产中对步进电机运行时间和距离有精确要求的常见工况,设计一套步进电机S曲线控制算法,根据不同的运行要求灵活设定运动过程,设定较少参数即能规划整个运动路径,达到理想的运动效果。设计新型余弦S曲线,搭建MATLAB/Simulink仿真控制模型和硬件测试系统进行仿真和试验验证。结果显示电机实际加减速过程运行平滑,起步稳定振动小,设定参数下可以精确运行,与直接起停相比,运行效果有很大改善。新型余弦S曲线已在全自动号码机项目中得到实际应用。     

管道内壁四足爬壁机器人的运动学与步态规划

研究用于检测气体绝缘金属封闭开关（GIS）内部的负压吸附管道内壁四足爬壁机器人. 分别对机器人的腿部和机身进行运动学分析,采用改进的牛顿迭代法解决机身正运动学求解困难的问题. 对机器人沿管道轴向和圆周方向的爬壁运动进行步态规划,提出运动过程零冲击的轨迹规划方法. 使用Adams进行运动仿真,并在四足爬壁机器人样机上进行水平和垂直管道的全方位爬壁实验. 结果表明：机器人的运动轨迹与所规划的步态一致,运动过程中速度与加速度无突变,运动平稳,无明显冲击,运动学模型的正确性和所规划步态的合理性得到验证. 在GIS管道的实际检测应用中,实现机器人在不同工况下的平稳爬壁运动与检测.     

基于操纵平稳性的液压挖掘机轨迹规划方法

以既能达到良好的轨迹规划精度,又有优良的操纵平稳性为目标,提出了一种挖掘机器人的智能轨迹规划方法.以挖掘姿态角为优化变量;油缸进程和加速度梯度为双目标;位置盲角和最佳切削范围为约束建立优化数学模型,采用遗传算法寻找最优值.对3种规划策略：被动修正法、主动调整法和智能规划法进行了行程和速度梯度对比,结果表明,采用优化规划方法可以大幅减少液压系统冲击和振动,使挖掘机操纵更加平稳.     

冷弯型钢特点及其生产发展

介绍了冷弯型钢的特点、生产工艺流程及其应用。在阐述分析冷弯型钢国内外生产现状的基础上，探索了它发展的方向。     

主旋翼升力和机身姿态受限的模型直升机非线性控制（英文）

A nonlinear control is proposed for trajectory tracking of a 6-DOF model-scaled helicopter with constraints on main rotor thrust and fuselage attitude. In the procedure of control design, the mathematical model of helicopter is simplified into three subsystems: altitude subsystem, longitudinal-lateral subsystem and attitude subsystem. The proposed control is developed by combining the sub-controls for the corresponding subsystems. The sub-controls for altitude subsystem and longitudinal-lateral subsystem are designed with hyperbolic tangent functions to satisfy the constraints; the sub-control for attitude subsystem is based on backstepping technique such that fuselage attitude tracks the virtual control for longitudinallateral subsystem. It is proved theoretically that tracking errors are ultimately bounded, and control constraints are satisfied.Performances of the proposed controller are demonstrated by simulation results.