承力操纵装置性能试验台系统方案设计

介绍了一个飞机承力操纵装置性能试验台的实现机理、采用的方案,有助于增加读者对液压系统、液压性能试验台及液压伺服控制系统的了解。     

基于人工噪声神经网络BP算法的火箭发动机故障仿真与检测

研究了用于液体火箭发动机故障仿真与故障检测的神经网络ＢＰ算法。在ＢＰ算法中采用了加噪声等技术来避免系统误差陷入局部极小，训练出精度高（误差小于０．０２）的神经网络，试验表明：神经网络ＢＰ算法成功地用于故障仿真与故障检测。     

薄膜温度传感器的研制及应用

一种新型的薄膜温度传感器,采用真空镀膜的方法制作在涡轮叶片表面,两者构成一体,可以真实反应表面温度。传感器的质量小、响应快,对叶片内部换热和表面燃气流无干扰。 传感器的敏感元件为铂姥_(10)-铂热电偶,测温上限可达1000℃,测量精度为±3％。     

基于RBF神经网络的航空发动机故障诊断模型

利用某型发动机地面定检状态实测数据作为学习样本，采用径向基函数(RBF)神经网络建立发动机的故障诊断模型。通过该模型对起飞状态实测的发动机参数进行了辨识，结果表明：这种方法具有训练时间短、学习速度快、诊断精度高等优点。     

振动环境技术在直升机研制中的地位和作用

本文简要介绍直升机研制中的一些故障现象及排除方法。以某型号为依托,介绍排除振动故障的过程;和动力学减振隔振技术结合,加装吸振器,通过参数调整达到最佳效果。从而揭示了振动环境技术工作在整个直升机研制工作中的重要地位和作用。以数据和图表简单形象地展示这一过程和最后效果。     

卫星故障诊断的最优奇偶向量法

 提供一种卫星故障诊断方法以提高 GPS导航的完整性。该方法利用最优奇偶向量来检测和诊断卫星故障以提高卫星故障诊断的准确性。仿真结果显示,在故障幅值较小的情况下最优奇偶向量方法相比广义似然比方法可以提高故障的正确检测率和正确诊断率。该方法还可以缩短检测斜坡型故障的时间,从而提高了系统的可靠性。     

传感器故障检测、识别和适应方法

对现有的方法进行了研究，着重阐述用检测滤波器思想进行传感器故障检测、识别和适应的方法。并利用这些方法，对一个具体的模型设计一个传感器故障检测、诊断和适应系统。通过故障仿真计算，验证了本文提出的方法使用的有效性     

The Cassini Cosmic Dust Analyzer

The Cassini-Huygens Cosmic Dust Analyzer (CDA) is intended to provide direct observations of dust grains with masses between 10⁻¹⁹ and 10⁻⁹ kg in interplanetary space and in the jovian and saturnian systems, to investigate their physical, chemical and dynamical properties as functions of the distances to the Sun, to Jupiter and to Saturn and its satellites and rings, to study their interaction with the saturnian rings, satellites and magnetosphere. Chemical composition of interplanetary meteoroids will be compared with asteroidal and cometary dust, as well as with Saturn dust, ejecta from rings and satellites. Ring and satellites phenomena which might be effects of meteoroid impacts will be compared with the interplanetary dust environment. Electrical charges of particulate matter in the magnetosphere and its consequences will be studied, e.g. the effects of the ambient plasma and the magnetic field on the trajectories of dust particles as well as fragmentation of particles due to electrostatic disruption.The investigation will be performed with an instrument that measures the mass, composition, electric charge, speed, and flight direction of individual dust particles. It is a highly reliable and versatile instrument with a mass sensitivity 10⁶ times higher than that of the Pioneer 10 and 11 dust detectors which measured dust in the saturnian system. The Cosmic Dust Analyzer has significant inheritance from former space instrumentation developed for the VEGA, Giotto, Galileo, and Ulysses missions. It will reliably measure impacts from as low as 1 impact per month up to 10⁴ impacts per second. The instrument weighs 17 kg and consumes 12 W, the integrated time-of-flight mass spectrometer has a mass resolution of up to 50. The nominal data transmission rate is 524 bits/s and varies between 50 and 4192 bps.This revised version was published online in July 2005 with a corrected cover date.     

飞机起落架故障数据库模型与实现方法研究

讨论了民用飞机起落架故障数据库的结构模型，基于关系模型故障数据库故障树存储结构的表示及实现，详述了Treeview的基本功能和使用方法等内容。文章最后介绍了采用VFP建立Boeing737起落架故障数据库的部分功能。     

飞机维护信息产生逻辑的解析

目前飞机故障诊断领域的研究多从飞机故障数据起始,对飞机故障如何产生和处理少有涉及。若缺乏对源头数据的分析,很难将故障诊断模型与机载故障触发逻辑有效匹配。为此,提出要采取飞机故障诊断模型和机载系统设计思路相吻合的故障诊断模型设计方法,对机载系统的故障产生逻辑和处理方法进行了解析,为下一步故障诊断奠定基础。