歼击机高度分层试飞验证

针对采用气动补偿空速系统以改善测高系统精度的现代飞机 ,简要介绍了高度分层的要求 ;阐述了引起飞机空速系统位置误差的主要误差源并进行了分析 ;给出了通过 GPS速度法对歼击机高度分层试飞验证结果 ,并对试飞结果进行了分析和讨论 ;结果表明 ,所得到的试飞数据可为飞机气动补偿空速系统设计和高度分层试飞方法研究提供重要依据。     

硅氧氮陶瓷的先驱体法合成及性能的研究

用 Si Cl4为原料 ,通过水解和氨解的方法 ,制备了不同含氮量的硅氧氮先驱体。先驱体通过脱氨基原位聚合 ,再经过无机化转变成为成分均匀的硅氧氮粉体 ,用所得粉体热压烧结制备了硅氧氮材料。测试分析结果表明 ,氮的引入使氧化硅的析晶温度提高了 1 5 0℃ ;适量析晶显著提高材料的力学性能 ;烧结温度为 1 4 0 0℃时 ,氮的质量分数为 2 4 .3%材料的强度和韧性最大 ,分别达到 1 5 6 MPa和 1 .8MPa· m1 / 2 ,比 Si O2 基体的强度和韧性提高了 4 .5 8倍和 2 .2 5倍。     

混压式进气道与弹体一体化流场数值模拟

基于Favre平均的N－S方程和B／L代数湍流模型,采用Jameson格式和矩阵人工粘性,对X布局的混压式超声速进气道与弹体的一体化流场进行了数值模拟,研究了解决了数值计算中的附面层抽吸及混压式进气 启动问题,得出了进气道内外流场的马赫数分布和速度分布,讨论了绕弹体非均匀来流条件下,进气道的位置,附面层抽吸及攻角对进气道性能的影响和进气道外型形状对弹性气动力的影响,结果表明,对混压式进气道必须进行附面层抽吸,进气道的位置对进气道的性能有很大的影响,进气道的外型型面对弹体的气动性能有一定的影响。     

The Lunar Reconnaissance Orbiter Diviner Lunar Radiometer Experiment

The Diviner Lunar Radiometer Experiment on NASA’s Lunar Reconnaissance Orbiter will be the first instrument to systematically map the global thermal state of the Moon and its diurnal and seasonal variability. Diviner will measure reflected solar and emitted infrared radiation in nine spectral channels with wavelengths ranging from 0.3 to 400 microns. The resulting measurements will enable characterization of the lunar thermal environment, mapping surface properties such as thermal inertia, rock abundance and silicate mineralogy, and determination of the locations and temperatures of volatile cold traps in the lunar polar regions.     

V型肋片直冷却通道内流动与传热的数值研究

采用结构化六面体网格和k-ε湍流模型求解三维N-S方程,对内置不同肋间距与肋高比V型扰流肋片的直冷却通道,在入口雷诺数为20 000时的流动与换热特性进行数值模拟,分析了不同肋间距与肋高比对肋间壁面换热效果和流动损失的影响,并对肋间距与肋高比进行了全局寻优。结果表明,带肋直冷却通道的整体换热效果和综合冷却效率,分别和肋间距与肋高比呈近似函数关系,肋间距与肋高比为7.93时通道整体换热效果最好,为5.2时通道综合冷却效率最佳。     

Numerical simulations of the radiance from the comet 46P/Wirtanen in the various configurations of the measurements during “Rosetta” mission

The work we present deals with the spectrometric measurements of VIRTIS instrument of the Comet P/Wirtanen planned for the Rosetta mission. This spectrometer can monitor (VIRTIS M channel: 0.250μm – 0.980μm; Δκ=20cm⁻¹; 0.980 – 5.0 μm; Δκ = 5cm⁻¹; VIRTIS H channel: 2.0 μm – 5.0 μm; Δκ=2cm⁻¹) the nucleus and the coma in order to provide a general picture of coma's composition, the production of gas and dust, the relationship of coma production to surface composition and the structure and variation of mineralogy of the nucleus surface. During the mission the observation conditions of the spectroscopic investigation change due to different relative positions spacecraft/comet, and to the different illumination conditions of the surface at various distances of the comet to the Sun. The nucleus surface is continuously modified by the ice sublimation accompanied by gas and dust emission. Consequently the surface also its spectrophotometric properties changes and their monitoring can give a new insight. The important role of simulations is to predict the results of measurements in various experimental condition what, in the future, can help in interpretation of the measured data.

In this paper the first results of our simulation the radiance from the comet in the 0.25–5.0μm spectral range at two distances from the Sun (1AU and 3AU) are shown. The distance between the Rosetta orbiter and the nucleus surface as well as the sun zenith angles are taken into account according to the Rosetta mission phases. In fact the surface and coma properties vary along the comet orbit, and should be taken into account in our calculations. The optical parameters of the dust on the surface (e.g. reflectance) and in the coma (e.g. Q_ext) were calculated from optical constants of possible comet analogues. The thermodynamic parameters of the comet are taken from the models of comet evolution. Through this kind of modelling it is possible to identify the surface characteristics in spectra of the radiation from the surface of nucleus transmitted through the coma loaded with dust and gases.

Even if the “Rosetta mission” is postponed, with the consequence of a target change, we think that our idea and the method used for the simulations can be useful also for the new Rosetta target - the comet 67P/Churyumov Gerasimenko.     

从自由试验提取具有弹性支承的阻尼约束结构的主模态

作者已对边界固持(即刚性支承)的无阻尼和有阻尼的约束结构，从自由试验提取其实模态和主模态的方法进行过系统的研究，同时，对于具有弹性支承的无阻尼约束结构模态的提取，也建立了一种可行的方法。这些方法和技术途径都取得了良好的结果，仅剩下具有弹性支承的阻尼约束结构主模态的提取方法尚无。对此，本文企图建立一种工程中可行而实用的方法。在该方法中，阻尼分为瑞利阻尼和粘性阻尼两种模型，这样，可以根据不同结构选用不同阻尼模型下的提取方法。数值模拟结果表明，本文建立的方法虽然不像以前无阻尼下的类似方法那样，具有普遍性，即取任何支承刚度(可以很大或很小)都可获得满意结果。不过，对于工程中常见的支承刚度比结构刚度大或等量级的实际情况，本文方法是能取得满意结果的。这表明，本文方法已基本满足工程要求了。     

基于有色载入技术的天基雷达信号处理方法

为了消除天基监视雷达非稳态杂波图景的影响,文中讨论一种利用有色载入（Colored-loading,CL）技术计算杂波协方差矩阵的空-时自适应处理（Space-time adaptive processing,STAP）方法。首先根据先前相干处理间隔（Coherent process interval,CPI）立体数据和先验知识,对杂波区域分块定位。并根据最大似然估计准则,估计各杂波块回波强度。对杂波回波强度进行归一化,并在多个CPI上取平均,得到杂波反射特性地图。结合该地图和先验知识,计算当前CPI的杂波协方差修正矩阵,将该修正矩阵有色载入当前CPI的杂波协方差矩阵,并对有色载入后的协方差矩阵进行主要特征值分析和重构。仿真结果表明,在天基雷达杂波环境中,该知识辅助CLSTAP算法远优于传统的滑窗处理（Sliding window processing,SWP）STAP算法性能,且与理想STAP算法的性能接近。     

考虑星-箭动力耦合作用结构瞬态响应分析

利用直接激励法，对火箭发射过程中考虑星箭动力耦合作用的卫星结构瞬态响应问题进行了求解。给出了最大动压、一二级分离前和分离后三种工况下卫星结构的加速度响应历程。该方法克服了大质量法和惯性载荷法瞬态响应计算中的载荷处理困难和数据回归困难。文中给出了大质量法、直接激励法和惯性载荷法的动力学方程，指出各种方法的应用条件。计算结果表明，直接激励法简捷实用，优于惯性载荷法和大质量法。     

电机智能制造信息化平台

通过对电机制造工艺的分析,以及实地调研电机生产企业运行现状的基础上,针对电机制造工艺复杂、人工依赖大等特点提出了一种电机智能制造信息化平台建设方案。就整体信息系统提出了基于电机行业的工厂模型建立以及系统集成的建议,为电机行业建设智能制造工厂、优化生产管理提供参考。