运载火箭可延伸喷管比冲增益的折合算法

本文在多级火箭理想末速度公式的基础上，推导了可延伸喷管有效比冲增益的计算公式，并对某三级固体运载火箭进行计算，得到了三种状态下可延伸喷管的有效比冲增益     

QCM用于检测航天器表面污染的技术研究

文章简要叙述了QCM(石英晶体微量天平)检测技术在航天器表面污染检测中的作用,主要体现在航天器表面、光学仪器和动力系统的污染检测,低地球轨道空间的原子氧检测,并且对QCM检测中使用的关键方法,热解重量分析法和温度效应进行分析。     

In-situ photopolarimetric measurements of dust and gas in the coma of Halley''s comet

The Halley Optical Probe Experiment (HOPE) on board the Giotto spacecraft has provided the first in-situ measurements, both of the dust and of some gaseous species, from inside the coma of the comet. The instrument has already been described /1/, together with first results /2/. The purpose of this note is to show how optical measurements can lead to in-situ information, how those were obtained during the 13–14 march 1986 Halley fly-by, and what is the status of the data analysis.     

一种民用飞机后储藏室的构建及适航验证思路

民用飞机的储存设备是飞机运营时需要使用的一类设备,可用于储存乘客、机组人员携带的物品及飞机型号设计中需要使用的设备。阐述了储存设备（隔间）的适航要求,并以某型号民用飞机上的后储藏室为例, 详细地阐述了其构建思路及对相应适航条款的验证思路。     

星载L波段宽带低噪声放大器芯片设计

基于0.25μm 砷化镓赝品高电子迁移率晶体管（GaAs pHEMT）工艺，设计了一款应用于星载微波接收机的L波段单片微波集成电路（MMIC）低噪声放大器（LNA）。该低噪声放大器采用电流复用拓扑结构，降低了芯片的工作电流，节省了宝贵的卫星能量资源；通过两级负反馈方式优化了器件的稳定性和增益平坦度，提高了卫星通信质量；恒流源的偏置结构使得工作电流随工艺波动较小，芯片维持在稳定的工作状态下。测试结果表明：该放大器工作电流为35mA，在频率范围0.9~1.8GHz内，增益大于33dB，噪声系数小于0.6dB，增益平坦度小于0.5dB；芯片尺寸为2.0mm×1.3mm，满足航天产品的高性能小型化应用需求。     

Time variations of the total electron content in the Southeast Asian equatorial ionization anomaly for the period 2006–2011

This study presents the time variations of the total electron content in the South East Asian equatorial ionization anomaly. The time variation of the TEC is analyzed through the period 2006–2011 by using a latitudinal chain of GPS stations extending in the northern and southern hemisphere. The data shows that the shape of the diurnal variation of the TEC depends on the latitude: a plateau is observed at the stations near the equator and a Gaussian at the station distant from the equator. We observe a semiannual pattern in all the stations with maxima at equinox. In both hemispheres, the amplitude of the crest is larger in spring than autumn from 2006 to 2008 and smaller in spring than in autumn from 2009 to 2011. We also observe an asymmetry between the amplitude and the position of the two crests of ionization. There is a very high level of correlation between the amplitude of the TEC at the two crests and the sunspot number: ∼0.88. During the deep solar minimum 2008–2009, the amplitude of crests of ionization becomes small during several months in summer and winter. The results show that both crests move significantly equatorward in winter than other seasons and there is a tendency for both crests to appear earlier in winter and later in summer.     

计算机与电视机显示转换的方法

介绍一种基于计算机ＴＶＧＡ８００×６００显示模式下，将计算机显示的图文信息正确地映射到ＰＡＬ制式彩色视频显示标准区域５１２×５７６内的方法，也就是将８００×６００逐行扫描显示模式的内容映射到５１２×５７６隔行扫描显示模式区域之中，使之完全符合ＰＡＬ制式行场同步标准，采用这种方法制作的图文电视具有图文满屏显示和分辩率高的特点。     

一种翼身融合飞行器的失速特性研究

翼身融合（BWB）布局飞行器作为下一代商用飞机的主要构型之一，越来越受到重视。对于翼身融合飞行器的研究主要针对其巡航状态的特性，而对其失速特性的研究较少。对一种翼身融合客机构型进行风洞试验研究，采用测力试验方法对其无增升装置的构型，以及具有翼梢小翼、前缘缝翼和机身上部双吊舱的组合部件构型下的纵向特性进行研究，特别是对其失速特性的分析，并通过二维粒子图像测试技术以及油流试验对其失速过程的流动机理进行研究。结果表明，无增升装置的基本构型下，翼身融合飞行器可以保持低速飞行，而各组合构型都具有提高最大升力系数的作用。对失速过程的分析表明，随着迎角的增大，飞机表面流场分离区域从翼梢开始逐渐向翼根以及机身发展，当外翼段完全处于分离区域时，飞机并不会马上失速，因为中心体同样具有提供升力的作用，且中心体的流动分离较外翼的流动分离更晚，所以当外翼在失速迎角出现升力损失时可以通过中心体的升力进行补偿，维持其低速飞行状态，真正的失速发生在中心体出现流动分离之后。     

航班延误赔偿现状及乘客过激行为的分析与预防

航班延误产生的矛盾会导致乘客采取过激的方式维权,这对民航运输安全造成了很大的影响。本文分析了航班延误后旅客采取的过激维权行为的原因,并从不同角度提出了预防措施,希望能对避免航班延误后乘客和航空公司发生矛盾以及采取过激维权行为有所裨益。     

Equivalent mechanical model for liquid sloshing during draining

For a spacecraft draining liquid fuel during a continuous thruster maneuver, a brief equivalent method is proposed to model the time-varying properties of liquid sloshing for dynamics and control design. The sloshing liquid during draining is equivalent to a set of mechanical model with variable parameters. The model parameters for sample filling ratios are determined by an efficient finite element method according to equivalent principles, while the parameters for other filling ratios are obtained by piecewise linear interpolation. Using the proposed model, forces and torques acted on a Cassini shaped tank by the inside liquid during draining are investigated undergoing several typical motions. Verifications and comparative studies are done with Computational Fluid Dynamics simulations, which confirm the accuracy of the brief model while the sloshing amplitude is small and the flow rate is low.