K—8飞机操稳特性试飞

主要介绍Ｋ－８飞机在鉴定试飞中的操纵性，稳定性试飞方法和结果，其中包括起飞，着陆，速度稳定性，过载稳定性，机动点，中性点的确定，同时还对纵向模态特性，横侧静稳定性，操纵性，滚转效率，横侧动态特性进行了测定，并在各特性的测定中谈了飞行体会。     

旅客航站楼规划设计的思考

建设一流的机场，必须有一流的设计，机场跑道确定后旅客航站楼的规划设计历来都是机场设计的核心，其中值得研究，探讨的问题颇多，国内外部在不断地探索和实践，文章根据近几年来在进行旅客航站楼的规划设计中，对一次规划，分期建设，滚动发展之间的衔接，功能性与民族形式，国内设计航站楼的安全等级与国外相同规范的差距，以及旅客站楼工艺流程的设计等问题，进行了有益的思考，并提出一些新的看法，供研究与探讨。     

中国应对经济全球化的关键在于培育优势产业

世界经济全球化所催生的产业全球化，加速了各国产业结构的调整、优化、升级。对中国而言，在全球化新的国际分工格局下，立足于比较优势的劳动密集型产业，曼然有较大的发展空间，但其技术含量低，附加值低，处于全球化的劣势地位，继续发展必然使产业固化，难以升级，也无法在激烈的全球竞争中获胜，最终将拉大我们与发达国家的差距，显然不能作为我国产业调整的方向；相反，放眼于发展战略的资本、技术密集的前景产业，虽然面临巨大的冲击，但它具有广阔的发展前景，有无限发展潜力和长久竞争优势，发展它们本身就是产业结构的提升，不仅可以缩小我们与发达国家的差距，而且有助于促进全面小康目标的实现。     

基于神经网络的稳M数非线性控制

介绍风洞稳Ｍ数神经网络的非线性控制，包括预测模型，动态优化和反馈校正原理，以实现速度快，精度高，低耗油的优化控制目标，试验表明，该系统不仅稳Ｍ数控制精度高，响应速度快，而且鲁棒性好，节省燃油。     

“十五”民航发展与飞行人才培养

一、“九五”回顾 “九五”期间，我国民航业经历了市场经济的严峻考验。面对前所未有的困难局面，行业上下齐心协力，团结一致，通过深化管理体制改革，加强宏观调控，规范航空运输市场，强化运价管理，调整航空运输结构，加强规章制度建设等一系列强有力的措施，冲破了由卖方市场变买方市场，由高增长变低增长，由高效益变低效益的重重困境，运输生产取得了可喜的成绩。 伴随民航业的发展，“九五”期间，民航飞行学院抓住历史机遇，不断深化以教学训练为中心的各项改革，通过更新训练机型，加大基础建设投入，完善训练设施，合理调整训练…     

利用GPS提高测量船的测位和测姿精度

测量船是海上活动观测站，船上配有精密跟踪测量雷达和光学经纬仪等测控设备，要精确观测空间飞行器的运动轨迹或弹道，就必须精确测定船体的位置，速度，姿态和航向，我国早期测量船上的导航系统使用避限性很大，而且相当落后，已经不能满足当代海上作业的精度要求，急需更新。目前，我国GPS已全面投入运行，利用该系统测定测量船的位置和姿态，不仅精度高，实时性强，而且操作简便，设备成本低，借助差分导航，组合导航等技术还可以进一步提高其定位测姿精度，不久的将来，俄罗斯的Glonass也将投入运行，且工作性能与GPS基本一样，可作GPS的补充导航能力。     

论试飞机场管理问题

由于航空事业的发展，对试飞提出了更高的要求，试飞工作量也在不断增加，新机种，新设备的试飞，又要求试飞机场具备相应的地面保证功能，因此对试飞机场原有的设备，也提出了更新，改造的问题，同进也提出了新的管理问题，这些问题在我们试飞院机场尤为突出，本文通过试飞院机场在使用中表现的问题，作一些分析，对如何搞好试飞机场的管理工作，谈一些个人的体会和意见。     

我校学生思想政治状况调查报告

近期我们对我校５６０名学生进行了问卷抽样调查，调查共发出问卷５６０份，回收５６０份，回收率为 １００％，全部为有效问卷。为确保调查的客观性、科学性，在抽样过程中，我们充分考虑了专业特色、学制特色，其中中专生１７５人，占３１．３％，高大专１７８人，占３１．８％，五年制大专２０７人，占３７％；电气系２０７人，占３６．９６％，机械系１７８人，占３１．７８％，计算机系８４人，占１５％，动力系５０人，占８．９％；从家庭来源看，大中城市６１人，占１０．８％，城镇１３０人，占２３．２１％，农村３６８人，占６５…     

用火焰原子吸收光谱法测定飞行员头发中Ca,Mg,Cu,Pb,Fe,Zn？…

人发样品是生物类有机样品，用火焰原子吸收光谱法测定人发中Ｃａ，Ｍｇ，Ｃｕ，Ｐｂ，Ｆｅ，Ｚｎ元素时，采用硝酸：高氯酸＝４：１消解体系，电热板加热常压消解大约２小时，样品呈湿盐态，以去离子水稀释定容，测定溶液为无色，透明，分别上机测定以上各元素，本测定方法技术关键在于消解温度不得超过２５０℃消解完全后要赶尽高氯酸，测定Ｃａ，Ｍｇ时，用０．１％ＳｒＣｌ２水溶液定容，以消除共存物的干扰，对各元素的仪器测定     

寓军于民 开创民机发展新局面

我国民用飞机工业的发展又到了生死存亡的关键时刻，如果 再不能抓住机遇，后果将不堪设想，所以我们必须立即停止争论，踏踏实实地进行结构调整，实现强强联合，充分利用现有的资源和体系，调动各方面的积极性，坚持以自力更生为主，尽快发展出我国的新支线飞机，同时也必须强化军用飞机的发展因为只有有了强大的军机工业，才能有强大的民机工业，才能真正实现我国航空工业的腾飞     

Abnormal Shape Mould Winding

为解决网格化芯模的缠绕问题,本文提出了复合材料面片缠绕机理;接着详细分析了面片缠绕过程中的芯模凹曲面上纤维滑线和架空现象,应用微分几何曲面理论和空间几何理论,提出判据及其解决方案;最后,针对飞机发动机进气道的缠绕成型,编制缠绕控制程序并进行相应的实验,验证了面片缠绕方法的可行性。     

Investigation of Formation Process of the Chrome-free Passivation Film of Electrodeposited Zinc

The feasibility was investigated to substitute chrome-free passivation treatment of electrodeposited zinc in a titanium bath for chromate passivation treatment. The formation mechanism of the chrome-free passivation film was further analyzed. The surface mor- phologies and the elemental compositions of the treated samples with varied immersion times were observed by scanning electron mi- croscopy (SEM) and determined by energy dispersion spectrometry (EDS), respectively. The electrode potential of the sample surface was recorded in the film formation process. The changes of the electrode potential are in accordance with that of SEM and EDS of the sample surface. The results of X-ray photoelectron spectroscopy (XPS) show the chrome-free passivation film composed of ZnO, SiO2, TiO2, Zn4Si2O7(OH)2, and SrF2. The anode zinc dissolution and the local pH value increase due to the cathode hydrogen ion reduction process result in the formation of the chrome-free passivation film. The macro-images of the chrome-free passivation films formed on electrodeposited zinc show that the color of the film changes from blue to iridescence with the increase of the immersion times.     

Convergence Analysis of the Numerical Solution for Cathode Design of Aero-engine Blades in Electrochemical Machining

As a main difficult problem encountered in electrochemical machining （ECM）, the cathode design is tackled, at present, with various numerical analysis methods such as finite difference, finite element and boundary element methods. Among them, the finite element method presents more flexibility to deal with the irregularly shaped workpieces. However, it is very difficult to ensure the convergence of finite element numerical approach. This paper proposes an accurate model and a finite element numerical approach of cathode design based on the potential distribution in inter-electrode gap. In order to ensure the convergence of finite element numerical approach and increase the accuracy in cathode design, the cathode shape should be iterated to eliminate the design errors in computational process. Several experiments are conducted to verify the machining accuracy of the designed cathode. The experimental results have proven perfect convergence and good computing accuracy of the proposed finite element numerical approach by the high surface quality and dimensional accuracy of the machined blades.     

高超声速飞行器模型不确定性影响分析

吸气式高超声速飞行器具有严重的弹性机体和推进系统耦合的典型特征,其分析模型存在较大的不确定性,标称系统和真实系统之间存在偏差,因此研究不确定性对稳定性的影响对于控制器设计具有重要意义。针对典型的乘波体构型高超声速飞行器,建立了气动/结构/推进相互耦合的动力学模型,总结了建模中的不确定因素并将其以加性不确定模型的形式表示出来。以不确定性矩阵的最大奇异值为边界模型,以不确定性矩阵的H∞范数来表示不确定性因素对稳定性影响的大小,并通过不确定性矩阵的边界曲线分析不确定因素对模态特性的影响。结果表明,惯性因素的不确定性对稳定性的影响最大,而且其对飞行器的短周期模态和弹性模态均有较大的影响;同时,对于这一类飞行器的控制器设计必须考虑飞行器的弹性自由度。     

Effects of Mo on the Microstructure and Hydrogen Sorption Properties of Ti-Mo Getters

The effects of Mo on the microstructure evolution, porosity and hydrogen sorption properties of Ti-Mo getters are investigated in this work. The results show that the addition of Mo prolongs the densification process of Ti-Mo getters and results in a significant amount of sintered pores. With the Mo content increasing, the porosity of getters firstly increases reaching the maximum value as it at- tains about 7.5wt.%, and then drops. At the room temperature, the hydrogen sorption property of getters increases progressively with the Mo content increasing, but the tendency is not very clear before its content lies below 2.5wt.%. When the Mo content achieves about 7.5wt.%, the hydrogen sorption property proves to be the best. The discussion is made about the above mentioned phenomena inclusive of hydrogen sorption properties of getters under different activation conditions (from 500-750 ℃).     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

航天器返回地球的气动特性综述

航天器返回地球的飞行过程中,气动特性是实现将宇宙飞行速度减到落地前速度、保证再入飞行得到有效控制以及再入防热安全可靠的关键因素。针对简单旋成体气动外形、半弹道式再入控制、烧蚀防热类返回航天器,综述了返回地球过程中变化的空气流域特性、航天器周围的气体绕流环境、空气与航天器作用产生的动力学与热效应等。系统地给出了该类航天器的再入气动特性参数与飞行性能的共性规律,包括:气动阻力与再入减速、气动升力与再入轨迹控制、配平攻角与飞行稳定性、气动加热与防热,以及再入过程中不同气动特性航天器、气象条件变化等对再入飞行性能的影响规律。为航天器开展返回飞行过程的跨流域气动性能工程研制提供设计参考。     

基于自由尾迹方法的自转旋翼气动特性研究

为研究自转旋翼的气动特性,建立了自转旋翼的自由尾迹方法计算模型,并耦合桨叶挥舞运动模型和自转旋翼配平模型,建立了一种分析自转旋翼气动特性的方法。以某试验自转旋翼为算例对该方法进行了验证并运用该方法研究了自转旋翼的尾迹几何形状和桨盘诱导入流分布特性。研究结果表明:建立的自由尾迹方法计算模型可以满足自转旋翼气动特性分析的需求,相比传统的近似入流模型,该自由尾迹方法模型精度更高;前飞时自转旋翼尾迹随时间推移自桨盘处向桨盘后上方运动,水平面内自转旋翼尾迹畸变略小于驱转旋翼;自转旋翼桨盘诱导入流呈非均匀分布,从桨盘前缘到后缘,下洗入流大致呈不断增加趋势,在相同拉力水平下,自转旋翼90°方位角附近及桨盘后缘的诱导入流小于驱转旋翼。     

PREDICTION OF MECHANICAL PROPERTY OF WHISKER REINFORCED METAL MATRIX COMPOSITE: PART-Ⅰ. MODEL AND FORMULATION

Based on study of strain distribution in whisker reinforced metal matrix composites, an explicit precise stiffness tensor is derived. In the present theory, the effect of whisker orientation on the macro property of composites is considered, but the effect of random whisker position and the complicated strain field at whisker ends are averaged. The derived formula is able to predict the stiffness modulus of composites with arbitrary whisker orientation under any loading condition. Compared with the models of micro-mechanics, the present theory is competent for modulus prediction of actual engineering composites. The verification and application of the present theory are given in a subsequent paper published in the same issue.     

二维翼段颤振的μ控制

 采用超声电机作为作动器来实现含控制面的翼段颤振鲁棒抑制。针对作者设计的二维翼段颤振主动抑制系统，通过理论与实验相结合的方法，建立了考虑沉浮方向阻尼和作动器模型参数不确定性的控制系统模型，设计了μ控制器，并对控制器做了降阶处理。数值仿真和风洞试验表明，μ控制器可有效地抑制颤振的发生，将颤振临界速度提高23.4%。相对于H_∞控制器，μ控制器的控制效果和鲁棒性更好。