三点法EST测量直线度的误差分析

叙述了三点法误差分离技术测量回转体素线直线度误差的原理，分析了参数选择、测头间距误差、传感器标定误差、工件安装误差对测量误差的影响，探讨了对信号谐波和测量噪声的抑制措施，以提高直线度误差的测量准确度。     

空间重粒子击中卤虫卵的定位技术及其生物效应

为了能够估价空间重粒子对单个生物细胞的放射生物学效应,我们设计、制成了卤虫卵-核乳胶夹层式生物包.经搭载我国“8885”卫星飞行数天后回收.用图象分析仪研究了空间重离子在核乳胶上留下的径迹及其分布;并实验观察了卤虫卵的前期发育情况.看到:随星飞行过的卤虫卵与地面对照组相比,其发育能力明显降低,表现为孵化率低且发育时间推迟.实验表明:生物样品板-核乳胶影象定位技术能清楚而比较准确地给出卤虫卵(或其他生物细胞)受重离子作用的信息,是重离子生物效应及其作用机理研究的可行实验手段及分析方法之一.     

科学视算──新的计算系统

一种新型的数学仿真系统一科学视算系统的特点、需要解决的问题、系统模型以及系统的构成在文中作了介绍和分析。     

软件技术状态检查工具的研究

软件技术状态管理是保证软件技术状态的正确性、控制软件技术状态的不受控性、提高软件可靠性的有效技术保障 ,是软件质量管理的一个重要环节。本文简要介绍了该工具的开发背景、设计思想、功能、优点及应用前景     

等离子体在军事上的应用

简要介绍了等离子体的特性及其在现代战争中的应用。着重讨论了等离子体在隐身技术、巡航导弹防御中的应用 ,另外还分析了以等离子体作为动力的等离子体火箭和等离子体武器的原理。     

应用自定位技术提供高精度的弹道位置参数

本文介绍了对连续波雷达的多普勒频率信息,用自定位技术获得高精度的弹道位置参数的一种方法。通过一些试验弹道的仿真计算,其结果表明当观测误差噪声为白噪声时,该方法所提供的弹道位置参数将比目前由连续波雷达定位信息提供的位置参数,其精度有明显的提高。     

Spin-stabilized satellite magnetic attitude control scheme without initial detumbling

The angular motion of an axisymmetrical satellite equipped with an active magnetic attitude control system is considered. The dynamics of the satellite are analytically studied on the whole control loop. The control loop is as follows: preliminary reorientation along with nutation damping, spinning about the axis of symmetry, then precise reorientation of the axis of symmetry in inertial space. Reorientation starts right after separation from the launch vehicle. Active magnetic attitude control system time-response with respect to its parameters is analyzed. It is proven that low-inclined orbit forces low control system time-response. Comparison with the common control scheme shows the time-response gain. Numerical analysis of the disturbances effect is carried out and good pointing accuracy is proved.     

防热材料热解与氧化性能试验技术研究

介绍了利用Arrhenius方程开展材料烧蚀热解性能动力学特性的基本原理，试验测试方法。并通过对炭酚醛材料烧蚀动力学参数的高频等离子体风洞试验研究，验证了采用时间历程积分在试验结果处理中的可靠性，在此基础上采用平板试验技术获得炭酚醛材料在600～1200K温度范围内的表面质量烧蚀率动力学方程，并将该方程所预测的结果与采用驻点烧蚀技术所获得的结果进行比较。结果显示：二者最大误差不超过5％，通过理论初步分析了二者之间存在差异的主要原因，并在试验比较分析的基础上，采用最大误差限理论分析了试验结果的可靠性。     

无人机载SAR一体化显控系统的设计研究

阐述了无人机载SAR一体化显控系统的设计,对系统实现中应用到的一些关键技术进行了详细说明,就多位面技术、多线程技术及内存映射技术进行了探讨。     

Spacecraft formation-containment flying control with time-varying translational velocity

This paper investigates the problem of Spacecraft Formation-Containment Flying Control (SFCFC) when the desired translational velocity is time-varying. In SFCFC problem, there are multiple leader spacecraft and multiple follower spacecraft and SFCFC can be divided into leader spacecraft’s formation control and follower spacecraft’s containment control. First, under the condition that only a part of leader spacecraft can have access to the desired time-varying translational velocity, a velocity estimator is designed for each leader spacecraft. Secondly, based on the estimated translational velocity, a distributed formation control algorithm is designed for leader spacecraft to achieve the desired formation and move with the desired translational velocity simultaneously. Then, to ensure all follower spacecraft converge to the convex hull formed by the leader spacecraft, a distributed containment control algorithm is designed for follower spacecraft. Moreover, to reduce the dependence of the designed control algorithms on the graph information and increase system robustness, the control gains are changing adaptively and the parametric uncertainties are handled, respectively. Finally, simulation results are provided to illustrate the effectiveness of the theoretical results.