航天产品计算机集成制造系统研发项目管理组织结构研究

通过分析复杂航天产品的研制特点,利用现代项目管理的理论和方法,阐述了建立平衡矩阵组织结构等组织管理手段,有效地解决了航天产品计算机集成制造系统研发项目组织管理中存在的问题,为军工制造业数字化项目的实施提供可借鉴的管理经验。     

高校计算机应用创意人才的培养途径探索

本文在分析了知识经济、信息时代催生的创意经济发展对计算机应用人才需求变化的基础上,结合高校培养计算机应用人才的培养和就业现状,探索了市场所需的计算机应用创意人才的知识技能特征及高校培养途径。     

钛合金导管的涡流检测

通过对大批量的钛合金管材进行涡流检测,从涡流检测原理以及影响因素等方面分析了缺陷信号、噪声信号的产生以及差异,通过多次调试试验得到了各种规格管材的检测参数,其中对检测结果影响比较大的频率、增益进行了多次对比试验,得到了最佳参数范围,为管材的可靠性判断提供了依据.     

Matrix Power Control Algorithm for Multi-input Multi-output Random Vibration Test

 Both auto-power spectrum and cross-power spectrum need to be controlled in multi-input multi-output (MIMO) random vibration test. During the control process with the difference control algorithm (DCA), a lower triangular matrix is derived from Cholesky decomposition of a reference spectrum matrix. The diagonal elements of the lower triangular matrix (DELTM) may become negative. These negative values have no meaning in physical significance and can cause divergence of auto-power spectrum control. A proportional root mean square control algorithm (PRMSCA) provides another method to avoid the divergence caused by negative values of DELTM, but PRMSCA cannot control the cross-power spectrum. A new control algorithm named matrix power control algorithm (MPCA) is proposed in the paper. MPCA can guarantee that DELTM is always positive in the auto-power spectrum control. MPCA can also control the cross-power spectrum. After these three control algorithms are analyzed, three-input three-output random vibration control tests are implemented on a three-axis vibration shaker. The results show the validity of the proposed MPCA.     

透波材料高温介电性能评价表征

概述了透波材料高温介电性能评价表征的研究意义及相关的基本概念、测试方法;介绍了国内外发展现状,以高Q腔法为例阐述了高温测试中关键共性技术,并对典型测试结果进行了分析;展望了透波材料高温介电性能评价表征的发展及应用前景.     

航空嵌入式软件测试环境确认方法研究

通过对国军标与DO-178B对航空嵌入式软件测试环境确认要求的对比与分析,提出了一种满足国军标与DO-178B要求的航空嵌入式软件测试环境确认方法。实际运用表明,方法灵活、高效、可操作性强,可以满足航空嵌入式软件测试环境确认的要求。     

高精度导航计算机实现技术研究

惯性导航系统是一种自主式导航系统,其核心部件是导航计算机。介绍了导航计算机实现的技术原理;分析了导航计算机实现的关键技术,包括高精度浮点处理技术、导航传感器功能集成技术、高精度导航技术、智能接口技术和集成化的软件开发调试环境;针对惯性导航系统对精度和实时性的要求,提出了一种高精度导航计算机的设计方案,其实现技术先进,具有广泛的应用前景。     

CJ1飞行模拟机座舱设备仿真实现及常见故障排除

介绍了加拿大Mechtronix电子有限公司生产的CJ1飞行模拟机各类仿真座舱设备以及实现的原理,着重提出了针对各类故障的不同解决方案和步骤,以及使用这类设备的优缺点.     

飞机喷口滑油泵斜盘操控性能的试验系统研制与调试

为在规定的θ-P试验条件下检测斜盘操控性能,喷口滑油泵测试液压系统中设置了3个固定孔径的节流器.通过对斜盘扭矩测试的试验方法、步骤及试验设备的介绍,以正向节流孔参数确定为例,建立了系统压力P与油泵斜盘角度θ的方程式,并通过标准泵的预置节流孔试验,获得了与油泵和节流孔结构形状有关的系数.再采用维算-试验测试-对比修改的试...     

Modeling and identification of an electro-mechanical system: The LISA grabbing positioning and release mechanism case

In the frame of space missions, mechanisms often constitute critical systems whose functionality and performance need to be tested on ground before the mission launch. The LISA scientific space mission will detect gravitational waves by measuring the relative displacement of pairs of free-floating test masses set into geodesic motion onboard of three spacecrafts. Inside each satellite, the injection of the test masses from the caged configuration into the geodesic trajectory will be performed by the grabbing positioning and release mechanism. To provide a successful injection, the test masses must be dynamically released with a minimal residual velocity against adhesion with the holding device. A parameter that determines the test mass residual velocity is the quickness of the retraction of the holding device. The need arises then to characterize the dynamic response of the release mechanism in order to predict its behaviour in the in-flight conditions. Once a validated model of the mechanism is available, the compliance of the system to the tight requirement on the maximum allowed residual velocity of the test mass may be verified. Starting from an electro-mechanical model of the mechanism dynamics, this paper presents the results of the experimental identification of its relevant parameters.