给出了基于CANoe软件的特种车控制系统测试环境的设计方法,通过数据库的建立、界面的编制等步骤可以快速建立起方便高效的测试环境,并且给出了在两个特种车中成功运用的实例.

为保证活动发射平台转换装置在同升同降动作时多个支腿运动的同步性,避免因支撑力不均导致过载,造成台体结构损伤,针对活动发射平台转换装置提出一种基于无线传感器测量的转换装置位置测量方案,并设计一种基于位置反馈的全自动主从同步控制方案.试验表明该方案可实现转换装置高精度同步控制,且简单高效、灵活可靠,控制效果良好,解决了转换装置同步控制的技术难题.

针对新型火箭垂直度多级联合全自动调整的控制需求,通过对需求分析及原理解析,建立控制算法模型,构建一个与算法适配的控制系统.通过对控制系统测试结果数据分析,完成系统及算法的改进提升,解决一键式多级联合全自动垂调控制的技术难题.

针对新一代载火箭12点支撑调平需求,通过12点调平的理想过程与实际需求解析,分解建立控制模型,设计了一种多耦合因素下12点快速调平闭环控制算法,并利用样机台架进行测试,根据试验结果制定控制策略,实现新型平台多点调平控制技术创新研究及精度优化提升.

为确保某运载火箭活动发射平台在轨道上完成运载火箭的垂直转运任务,根据活动发射平台产品自身和转运轨道的技术特点,在借鉴以往型号设计经验基础上,设计了其理想速度曲线,包含直线轨道运行、经过道岔和终点定位等过程,通过行走试验证明活动发射平台理想速度曲线设计合理,能够保证活动发射平台在满足任务要求的基础上顺利完成运载火箭的垂直转运任务.

Based on the idea of cloud computing,this paper proposes an automated testing cloud platform solution for largescale computational fluid dynamics (CFD) software verification and validation.The main objective is to reduce labor costs,improve software quality and development efficiency,and be adapted to high performance computing for future development as well.This platform uses modularized browser/server (B/S) network architecture and LAMP (Linux+ Apache+ MySQL+ PHP/Python) development tools.A continuous integration professional database is established,and a cloud environment is built,covering reliable cluster computing,complicated operation scheduling and massively parallel computing.This solution is able to automatically load test cases,submit cluster computing,monitor real-time process,post-process automatically and export analysis results containing comparisons with detailed experimental data,error analysis and summary reports.This platform has been applied to a large-scale parallel computing CFD software,and the feasibility and practicability of this solution have been verified.

交流伺服电机具有定位精度高、响应速度快、启动转矩大、过载能力强的特点,广泛应用于对精度要求较高的机械设备中.本文以STM32F103单片机为核心,通过伺服电机驱动器,利用位置模式控制伺服电机,对基于伺服电机控制系统的设计具有一定的指导意义.

In order to keep the motility in the thin atmosphere,air vehicles usually employ reaction control system (RCS),but in supersonic flow,it leads to complex jet interaction flow field on the surface of air vehicles,which has enormous influence on flight control.In order to improve the regularity understanding of jet lateral control,a model without any vane and a model with four tail vanes were used to study the sonic jet control effects in supersonic cross-flow by numerical simulation.The investigation of the influence of the jet location on the jet lateral control was conducted and the quantitative analysis of the contribution of different characteristic regions on the sweep to the jet lateral control was given.The numerical results indicate that as to wing-body configuration,the backward moving of the jet location and the increase of Mach number observably improve the jet lateral control effect;the amplification coefficient of the jet interaction force increases with the increasing angle of attack,and decreases with the increasing static pressure on condition that the jet is located before the tail vane;however,the law is opposite on condition that the jet is located after the tail vane;wingbody configuration,compared to body-alone configuration,does not have advantages on jet lateral control effects under some jet location and flow conditions.

高超声速飞行器壁板在非定常气动力、热载荷和噪声载荷构成的多物理场联合作用下,将表现出复杂的非线性气动弹性声振响应,特别是在颤振临界动压附近,受热载荷以及声载荷作用,壁板表现出复杂的跳变运动.基于von Karman大变形板理论,建立了热-声载荷和气动力共同作用下的壁板运动方程,分析了超声速气流中受热壁板的屈曲变形及热屈曲稳定性,借助势阱概念初步分析了壁板跳变运动产生的机理.通过定义“穿零频次”给出了跳变运动定量的分类方法,并计算得到不同温升和动压情况下,壁板发生跳变运动所对应的临界声压级.结果表明:在颤振临界动压之前,随着动压的增加,受热壁板势阱的深度先增大后减小,且受热壁板的势阱深度随着温升的增加而增大.

描述了一种高可靠摆杆远程控制系统的组成、摆杆控制方法、远程冗余控制原理,以及摆杆控制通路的实现方式,采用基于热备冗余控制器和工业以太网构建的控制系统,能够可靠地实现设备的远程控制,大幅提高了设备可靠地完成任务的能力,并成功应用于新研制火箭的发射任务中.展望未来,该系统在各基地摆杆可靠性升级改造,以及电站、钢厂,以及其它要求远程控制、可靠性高的军用和民用控制领域均具有较高的应用价值.