民机营运维修保障系统仿真

阐述了民机维修保障仿真系统，并讨论了它与民机可靠性，维修性和经济性仿真大系统的关系。文中重点介绍了民机营运阶段维修保障系统仿真建模及其应用软件ＣＡＲＭＥＳ的功能模块设计，最后以国内某航空公司营运的Ｙ－７飞机为例对其ＲＭＥ进行分析和评价。     

世界航空动力技术的现状及发展动向

讲述了喷气战斗机动力的发展历程.推重比8一级发动机是目前世界各发达国家现役主战机种的动力,配装推重比10一级发动机的第4代战斗机预计在2003～2007年后陆续装备使用,成为美国、部分西方国家甚至我国部分周边国家和地区2010年后的主战机种.概括了民用涡扇发动机和直升机动力的发展及其主要关键技术.列举了21世纪航空动力主要关键技术的发展方向.     

基于可靠性管理平台的飞机结构工程管理

详细分析了飞机结构可靠性方案实施的重要环节，阐述了飞机结构工程管理的工作思路和实施方法，为航空公司的结构工程管理工作提供借鉴。     

大厚度比零件（外侧）和波纹管（内侧）的缝焊研究

某重点型号波纹管组合件的设计要求是缝焊，对照以往产品的结构，比较明显的情况是波纹管在零件的内侧。零件的厚度是3mm，波纹管的厚度是0.1mm，零件与波纹管的厚度比比较大。波纹管在零件的内侧会产生一个问题：波纹管在焊接过程中会逐渐收缩，到最后与零件之间产生间隙，导致局部形不成焊缝。研究通过减小车配间隙,增加冷却手段、滚轮厚度和压力等措施来实现大厚度比的零件和波纹管之间的缝焊。     

A320系列飞机机身抖动现象浅析

针对A320系列飞机在营运过程中产生间断性水平或垂直抖动故障，分析了产生抖动的原因，并通过更换作动器或操纵面铰链排除了抖动故障．同时提出了避免A320系列飞机交替产生不稳定因素的措施。     

波音757-200型飞机风挡加温系统故障的排除与总结

通过对一起波音757—200型飞机风挡加温系统故障的排除．对该型飞机风挡加温系统的组成及工作原理进行介绍，为类似故障的排除提供了借鉴经验。     

Suggestion for aircraft flying qualities requirements of a short-range air combat mission

Owing to the lack of a direct link with the operations in short-range air combat,conventional aircraft flying qualities criteria are inappropriate to guide the design of a task-tailored flight control law.By applying the mission-oriented flying qualities evaluation approach,various aircraft with different control law parameters are evaluated on a ground-based simulator.This paper compares the evaluation results with several conventional flying qualities criteria,and discusses the appropriate parameter combination to reflect the flying qualities requirements of short-range air combat,The comparison and analysis show that a short-range air combat mission requires a higher minimum short period mode natural frequency and a smaller maximum roll mode time constant,and allows a lower minimum pitch attitude bandwidth and a higher maximum short period mode damp ratio than those of conventional flying qualities criteria.Furthermore,a combination of the pitch attitude bandwidth,the pitch attitude magnitude at the bandwidth frequency,and the pitch attitude transfer function gain can define the flying qualities requirements of short-range air com bat.The new metric can successfully predict the flying quality levels of aircraft in a short-range air combat mission.     

翼身融合布局客机总体参数分析与优化

在翼身融合布局客机总体设计阶段，为评估设计方案的总体性能，建立了翼身融合布局客机总体参数综合分析与优化平台，该平台以翼身融合布局客机的几何参数为输入，完成动力、几何、重量、气动、性能和经济性等模块分析，并以此为基础建立优化设计模型。为快速评估设计方案的性能及优化设计效果，动力分析模块采用了部件级分析模型，重量分析模块采用半经验估算方法，气动分析模块采用面元法结合工程估算方法，性能分析模块采用简化运动学方法，优化模型采用可并行计算的子集模拟优化算法。以某555座级翼身融合布局客机方案为例，应用开发的分析与优化平台，完成了总体参数分析，结果表明分析模型合理。在此方案的基础上，以客机的外形参数和发动机海平面最大推力为设计变量，分别建立了以最大起飞重量最小为目标的单目标优化，以及同时以直接使用成本和进场速度最小为目标的多目标优化，单目标优化结果最大起飞重量降低了约7.17%，多目标优化结果表明直接使用成本降低8.77%的同时进场速度会增加3.32%。     

Hypervelocity impact induced shock acoustic emission waves for quantitative damage evaluation using in situ miniaturized piezoelectric sensor network

Manmade debris and natural meteoroids, travelling in the Low Earth Orbit at a speed of several kilometers per second, pose a severe safety concern to the spacecraft in service through the HyperVelocity Impact(HVI). To address this issue, an investigation of shock Acoustic Emission(AE) waves induced by HVI to a downscaled two-layer Whipple shielding structure is performed,to realize a quantitative damage evaluation. Firstly a hybrid numerical model integrating smoothparticle hydrodynamics and finite element is built to obtain the wave response. The projectiles, with various impact velocities and directions, are modelled to impact the shielding structure with different thicknesses. Then experimental validation is carried out with built-in miniaturized piezoelectric sensors to in situ sense the HVI-induced AE waves. A quantitative agreement is obtained between numerical and experimental results, demonstrating the correctness of the hybrid model and facilitating the explanation of obtained AE signals in experiment. Based on the understanding of HVI-induced wave components, assessment of the damage severity, i.e., whether the outer shielding layer is perforated or not, is performed using the energy ratio between the regions of ‘‘high frequency" and ‘‘low frequency" in the acquired AE signals. Lastly, the direct-arrival fundamentalsymmetric wave mode is isolated from each sensing signal to be input into an enhanced delay-andsum algorithm, which visualizes HVI spots accurately and instantaneously with different sensor network configuration. All these works demonstrate the potential of quantitative, in situ, and real time HVI monitoring using miniaturized piezoelectric sensor network.     

涡桨飞机发展现状及关键气动问题

独特的动力形式赋予了涡桨飞机优越的推进效率和良好的低速机动、起降性能，使得其在军用及民用领域占有重要的地位并得以不断发展，但同时也带来了一系列需要重点关注的设计问题。本文从目前国内外涡桨飞机的发展现状和设计特点出发，提出其面临的主要气动问题。重点针对国内亟待发展的舰载类涡桨飞机起降过程中的失速和操纵问题进行深入研究，剖析了翼面附近流动的分离状态和发展趋势对于失速特性及操纵安全性的影响规律，归纳总结出需要关注的关键约束和设计原则。在此基础上，通过对一组计算实例的分析，给出了机翼空间流场变化特征和宏观气动力之间的内在联系，并深入阐述了三维增升构型与干净构型及其各站位翼剖面的设计关联性。