一种弹目遭遇点预测方法

为充分利用舰空导弹中制导段所获信息并减小导弹中制导段的弹道曲率,给出一种弹目预测遭遇点的解算方法,并据此设计比例导引制导律。在初始发射坐标系中,假设目标由当前位置以当前速度大小沿当前速度方向匀速运动至遭遇点,导弹由当前位置以当前速度大小按照一定的导引规律匀速运动至遭遇点。在该假设条件下,导弹到达遭遇点的总航路大小一方面...     

基于参数化分析的柔性后缘优化设计

介绍了一种自适应柔性机翼后缘变形控制优化设计方法,该方法采用了由单个驱动器驱动的单块式分布柔性结构。该方法的关键在于设计一种合适的柔性后缘结构拓扑形式,使该自适应柔性机翼后缘能够达到精确的变形。阐明了柔性结构拓扑优化设计的数学模型,针对自适应柔性机翼后缘概念设计提出了基于参数化分析的拓扑优化设计方案,并进行了工程化圆整和尺寸优化。最终,通过非线性有限元分析和功能测试,验证了本文提出的柔性后缘优化设计方法的合理性。     

双环预混旋流燃烧室点熄火性能试验研究

为了通过试验方法获得贫油点熄火边界,以双环预混旋流低污染燃烧室为研究对象,分析主燃级径向旋流器的叶片角 度、旋转方向及多斜孔壁火焰筒的冷却孔偏转角等参数对燃烧室点熄火性能的影响。结果表明：主燃级旋流器叶片角度对燃烧室的 点火性能影响不大;火焰筒冷却孔有偏转角且方向与主燃级旋流器旋向相同时的点火性能优于旋向相反时的点火性能;预燃级旋 流器与主燃级旋流器旋向相反时,火焰筒冷却孔有偏转角且方向与主燃级旋流器旋向相同时的点火性能优于无偏转角时的点火性 能,旋向相同时,则无明显影响;火焰筒冷却孔无偏转角时,预燃级旋流器与主燃级旋流器旋向相反的贫油熄火性能优于旋向相同 时的贫油熄火性能。     

舱内航天服散热途径分析

为分析常压下航天员穿着舱内航天服时的散热性能，６名健康男性青年按二次复合设计分组共进行２４人次试验，经分析计算了获得了服装各散热途径的散热率随通风气源参数及人体活动水平变化的数学模型。对影响服装散热性能的因素及服装散热特性进行了分析讨论。     

The concept of selecting the main parameters of a lightweight airplane with regard to the requirements of the contemporary Russian market

The basic principles of selecting some design parameters of a lightweight airplane for the contemporary Russian market are presented. Recommendations for selecting these parameters with the service requirements specified are given based on the study performed.     

电子显示屏在高校图书馆工作中的应用

本文以北华航天工业学院图书馆的电子显示屏的使用为例,介绍了高校图书馆电子显示屏通过一定的控制方式显示文字、图形、二维或三维动画、电视等各种信息的方法,实现文本、图像、视频等多种内容形式的播放,彰显出电子显示屏在图书馆对外宣传服务中的优越性。     

Quaternion regularization and trajectory motion control in celestial mechanics and astrodynamics: II

Problems of regularization in celestial mechanics and astrodynamics are considered, and basic regular quaternion models for celestial mechanics and astrodynamics are presented. It is shown that the effectiveness of analytical studies and numerical solutions to boundary value problems of controlling the trajectory motion of spacecraft can be improved by using quaternion models of astrodynamics. In this second part of the paper, specific singularity-type features (division by zero) are considered. They result from using classical equations in angular variables (particularly in Euler variables) in celestial mechanics and astrodynamics and can be eliminated by using Euler (Rodrigues-Hamilton) parameters and Hamilton quaternions. Basic regular (in the above sense) quaternion models of celestial mechanics and astrodynamics are considered; these include equations of trajectory motion written in nonholonomic, orbital, and ideal moving trihedrals whose rotational motions are described by Euler parameters and quaternions of turn; and quaternion equations of instantaneous orbit orientation of a celestial body (spacecraft). New quaternion regular equations are derived for the perturbed three-dimensional two-body problem (spacecraft trajectory motion). These equations are constructed using ideal rectangular Hansen coordinates and quaternion variables, and they have additional advantages over those known for regular Kustaanheimo-Stiefel equations.     

Theoretical determination of shot peening process parameters

In this paper, a proper choice of technological parameters for a shot peening process is considered, namely, the shot diameter, shot blast velocity, density of shot material, and depth of a plastically deformed layer-depending on the material being processed. The data presented can be used in calculations of technological parameters of FV monolithic panel shaping.     

Microperturbations on the <Emphasis Type="Italic">International Space Station</Emphasis> during physical exercises of the crew

The results of a preliminary analysis of microperturbations on the International Space Station during physical exercises of the crew are presented. The goal of this paper is to identify the parameters of perturbations when physical exercises are performed. The results of measurements by sensors of microaccelerations of both Russian and American segments during physical exercises in the service module of the Russian segment are analyzed.