航空航天智能材料与智能结构研究进展

智能材料作为新兴多功能材料,能够实现结构功能化、功能多样化。智能结构是在结构中集成智能材料作为传感器和驱动器,使结构除了具有承载、传力、连接等功能外,还具有自感知、自诊断、自驱动、自修复等能力,以更好地适应外界环境的变化,可显著提升航空航天架构的性能。目前智能材料与智能结构已成为航空航天架构减重增效研究的重点。根据国内外智能材料和结构的研究进展,综述了压电材料、铁磁材料、形状记忆材料、智能复合材料等智能材料的发展;讨论了智能结构的研究及应用前景,包括自诊断智能结构、自修复智能结构和减振降噪智能结构;最后,指出了智能材料与结构当前面临的一些挑战性问题,展望了其在航空航天领域的应用前景。     

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Spacecraft that are launched to operate in Earth orbit are susceptible to impacts by meteoroids and pieces of orbital debris (MMOD). The effect of a MMOD particle impact on a spacecraft depends on where the impact occurs, the size, composition, and speed of the impacting object, the function of the impacted system. In order to perform a risk analysis for a particular spacecraft under a specific mission profile, it is important to know whether or not the impacting particle (or its remnants) will exit the rear of an impacted spacecraft wall. A variety of different ballistic limit equations (BLEs) have been developed for many different types of structural wall configurations. BLEs can be used to optimize the design of spacecraft wall parameters so that the resulting configuration is able to withstand the anticipated variety of on-orbit high-speed impact scenarios. While the level of effort exerted in studying the response of metallic multi-wall systems to high speed particle impact is quite substantial, the extent of the effort to study composite material and composite structural systems under similar impact conditions has been much more limited. This paper presents an overview of the activities performed to assess the resiliency of composite structures and materials under high speed projectile impact. The activities reviewed will be those that have been aimed at increasing the level of protection afforded to spacecraft operating in the MMOD environment, and more specifically, on those activities performed to mitigate the mechanical and structural effects of an MMOD impact.     

数字化组合式大力值校准系统的研制

为了满足对大力值(20 MN左右)的测量和校准,开发了一套数字化组合式大力值校准装置。其最大量程可达24 MN,系统测量准确度为0.1%,适合于大型材料试验机的校准和检定。本文详细介绍了装置的组成结构、弹性体设计、贴片和组桥方式、数字化的方法以及与计算机的通信实现。     

利用气动式溜车—管路系统实现散状物料的输送

气动式溜车－管路系统是近年来兴起的一种高效的中，长距，离输送装置，它克服了常规运输系统运费高，噪声大和污染环境的缺点，在工程上有着良好的应用前景。本文对该系统的原理和原理和结构进行了较为细致的分析，并介绍了一个应用实例。     

复合材料层板纯剪实验

本文提出一个测量复合材料层板面内剪切性质的方板纯剪试验法。首先对方法的可靠性进行试验检验,然后对两种复合材料层板的剪切行为进行试验。     

结构比强度及其在优化设计中的应用

本文从结构重量角度推导了比强度(含比模量)表达式,分析了对同一材料不同比强度的关系,给出了比强度在结构动态分析中及结构优化设计中的应用。     

轻质隔热纳米孔结构耐烧蚀酚醛材料

在一定温度下,通过改性剂组分与热固性钡酚醛树脂之间热共聚反应,制备了改性酚醛树脂。采
用模压工艺制备出具有目标尺寸和形状的改性酚醛树脂固化物,对该样品分别进行了400 和700℃的炭化处
理,得到了相应的酚醛炭化样品,并测试其密度、失重率、收缩率等特征参数。研究改性剂用量对碳化物特征参
数和性能的影响,如密度、失重率形貌、比表面积、隔热性能、压缩强度等。SEM 研究表明,700℃炭化后样品形
成了“珊瑚状”碳结构,形成了30 ~150 nm 纳米孔。比表面积测试(BET)结果表明其比表面积可达464 m2 / g。
隔热性能与力学性能的测试结果表明,相对于未改性酚醛树脂碳化物,改性酚醛碳化物的热导率降低了
45． 57%,并且保持了较好的压缩强度。     

真空绝热板阻隔膜PA/ VMPET/ Al/ PE 热封工艺

真空绝热板阻隔膜PA/ VMPET/ Al/ PE 是一种多层复合阻隔膜,是真空绝热板的重要候选膜材。 通过实验研究了热封温度、时间、压力对其强度的影响,同时采用Matlab 软件对热封工艺参数进行优化,得出 最佳的热封工艺。利用DSC 对PA/ VMPET/ Al/ PE 进行热分析。实验结果表明:热封温度是影响热封强度的 最显著因素,当热封温度为160 ~170℃,热封时间为1. 0 ~2. 0 s,热封压力为0. 2 ~0. 4 MPa 时,热封边的热封 强度良好。Matlab 软件优化最佳热封工艺参数值为:热封温度167℃,热封时间1. 80 s,热封压力0. 34 MPa,该 模拟优化热封工艺参数与实验值一致。     

浅析俄罗斯战斗机CY—37“金雕”前掠翼三翼面气动布局的先进性

本文追溯了前掠翼的飞机的渊源。指出常规二翼面的后掠翼，变后翼和近矩耦合鸭式气动布局存在着妨碍机动进一步提高的缺点。     

ANALYSIS OF AN ELECTROSTRICTIVE STACK ACTUATOR FOR ACTIVE TRAILING EDGE FLAPS

Helicopter is a complex dynamic system withmany rotating components. The rotor blades oper-ate in a highly complex aerodynamic environment.The vibratory hub load,which is caused by cyclicvariation ofcentrifugaland aerodynamic load of therotating bladesin flight,is transmitted to the fuse-lage,resulting in serious vibration and noise of thestructure. It is one of the most important excitingsources in helicopters.There has long been a desire to reduce heli-copter vibration and to improve its per…