In order to improve the stability of the system in the process of cargo transfer and reduce the influence of the incompletely closed state of the dimensional chain, the research proposes a method of calculating the applicable value of the nonlinear driving force in the process of cargo transfer. In view of the characteristics of the goods transfer process, the analytical model of the transfer process is established by introducing the dynamics of shelves and goods in different states, and the acceleration trend of the system is obtained by adopting the plane motion characteristics of the rigid body, and then the analytical solution of the nonlinear driving force is given based on D'Alembert's principle. In order to further verify the correctness and accuracy of the nonlinear driving force, a typical intelligent storage system is used as a case study, and the analytical solution of the nonlinear driving force is verified based on the simulation method of the dynamics characteristics, and the results show that this method can significantly improve the computational efficiency under the premise of ensuring the accuracy of the calculation of the nonlinear driving force, which can effectively ensure the reliability and stability of the load transfer process.

机电伺服系统在航天应用中已初具规模,航天装备的特殊性决定了航天机电伺服系统对其体积、重量、可靠性、环境适应性的要求极为严苛,客观上对机电伺服技术发展提出了更高要求.在航天机电伺服系统研制的工程实践中,产生了具有自身鲜明特点的分析、设计理论和方法,推动着机电伺服技术的发展.其中,机电伺服系统的动态特性对伺服系统本身及飞行器的控制精度和振动等特性具有重要影响.针对机电伺服系统理论建模中结合部刚度难以确定的问题,以典型机电伺服系统结构为研究对象,根据机电伺服系统结合部的特点,提出基于Hertz接触理论的伺服系统动结合部刚度计算方法.所提方法为机电伺服系统动结合部刚度的识别提供了参考,研究结论可为机电伺服系统的改进设计和动态性能优化提供依据.

装备综合保障工程是装备体系建设的重要组成部分,是装备战斗力和保障力生成的重要支撑.随着信息化、体系化战争的深入推进,装备综合保障工作正向信息化、网络化、智能化方向发展.以未来作战形态和装备发展趋势为出发点,研究未来智能化装备保障需求,构想了一种基于"全球信息云+装备监控中心+分布式智能系统"组成架构的智能化保障系统方案.从维修保障、使用保障两个维度探索了智能化保障的运行模式,初步实现了装备保障的决策智能化与执行无人化,为逐步构建起适应未来战争发展的新型保障系统,支撑我军建设一支世界一流军队提供发展思路.

提出了一种通过液压系统控制的三自由度工业机器平台,着重介绍了三自由度机器平台的机械结构及性能指标参数.通过ADAMS、AMESim、Matlab/Simulink软件间的协同仿真技术开展了该机器平台的机电液一体化的仿真分析,确定所设计的三自由度机器人能够较好地跟踪给定的目标指令,满足系统设计要求.通过虚拟仿真,提高了机电液复杂系统分析的效率,仿真方法对于复杂机电液系统具有普遍的适应性.

Modal shear force and modal bending moment are the foundation of the calculation and identification of transverse dynamic load, the method of obtaining modal shear forces and modal bending moments of the missile with branch beam was improved. First, the modal shear forces and modal bending moments of the major beam and branch beam in the Beam-Mass finite element model were deduced from the definition of shear force and bending moment. Then, the flight loads of a missile under transverse static loads were calculated by mode superposition method, the results were compared to those of statics. It's showed that the results of mode superposition method gradually approach those of statics with the numbers of modes, they are the same when all the modes are included, so the method of obtaining modal shear forces and modal bending moments is verified.

The results of modal test included frequencies and mode shapes of specimen in different status and stages, so multiple objective functions were needed for model correction. A method of model correction of Timoshenko beam based on Pareto front was proposed. The model was corrected through global crossover and mutation, solving the noninferior solution set, defining new fitness of individuals and sorting the noninferior solution set according to crowding distance. The results showed that high precision can be achieved by this method and the Pareto front converged at nonconvex shape. Compared to the results of test, the deviation of the first natural frequency of the corrected model was less than 1%, the deviation of the second natural frequency was less than 6% and the mode shapes were in agreement with test.

Abstact:Timoshenko was the first tointroduce a shear coefficient to account for the variation of the shear stress along the cross-section, the shear coefficient was important to Timoshenko Beam. The effects of shear coefficients on the inherent characteristics of Timoshenko beam were studied. First, the dynamic model was established using FEM, the calculation methods of stiffness matrices were proposed for uniform beam and non-uniform beam, and then the influence of different coefficients on the frequency and mode shape of beam was discussed. The results show that shear coefficients bring about some influence on frequencies, but have little effect on mode shape; the precision of the model using the second shear coefficient is higher.

A method of dynamic property prediction based on structural similarity was proposed by this paper. First, the precise FEM model of the reference missile was achieved by model updating based on GA,then the correction coefficients were solved. According to structural similarity, the dynamical model of the new similar missile was setup using the correction coefficients of the reference missile, The test results have verified that, the deviation of the first three natural frequencies of the new model is less than 11%, and the first three mode shapes are in agreement with test.