数字信道化内插结构的一种推导方法

介绍了数字信道化内插结构的一种简便推导方法,该方法直接从第k个信道的内插结构开始推导。采用该方法推导了数字信道化的一种典型内插结构。对推导出的内插结构进行了Matlab仿真,验证了该方法的正确性。     

飞机电源系统故障诊断方法综述及发展趋势

飞机电源系统是机上一切用电设备的电能来源,其安全性与可靠性至关重要。在环保和高效发展需求的背景下,现代航空工业正在推进以电能为核心的多电/全电飞机技术的研究和应用。电驱动装置和电力电子器件的广泛使用导致飞机电源系统结构的复杂化,对飞机的可靠性、安全性、测试性和维修性提出了更高的要求,研究飞机电源系统的故障诊断技术具有重要意义。首先介绍了飞机电源系统的组成结构和各自功能,概述了飞机电源系统的发展历程,对比了国内外典型电源系统的特征,总结了飞机电源系统中的主要故障模式、故障特点和失效原因,并提出了一种飞机电源健康管理系统的设计架构,然后综述了国内外基于模型和基于数据的故障诊断方法研究进展,从准确度、数据需求量、适用性和实现难易程度等方面评述了各类诊断方法的特点,最后指出了飞机电源系统故障诊断技术面临的挑战和发展趋势。     

航天器结构材料的应用和发展

文章首先说明航天器结构材料的定义及其性能要求，然后简要介绍航天器结构材料的主要类型及其基本性能，并且综述航天器结构材料的应用概况，最后指出航天器结构材料的发展趋势。     

磁场全张量测量计算方法与误差分析

矢量磁场和磁场全张量数据是多磁源反演的数据基础。针对矢量磁场和磁场全张量的测量问题,文章提出了矩阵式矢量磁场连续扫描方法。对利用矢量磁场计算磁场全张量所用的数据结构进行了研究,应用MATLAB软件对常用的十字形和六面体两种不同数据计算结构进行了仿真分析,结果表明,两种计算结构的误差相近且均不大于10%;并分析了基线距离对磁场全张量计算的影响,结果表明,磁场全张量计算误差随着基线距离的增加而增加。     

全位置自动焊管机TIG焊电源研制

本文介绍了一种适用于管－管、管－板对接的全位置自动TIG焊晶体管电源，该电源采用可编程控制器控制，具有直流／脉冲功能，焊接参数在4个区间内可分别预测，试验表明，该电源区间过渡时电弧稳定，抗干扰能力强，焊缝均匀、连接。     

火箭发动机基于神经网络非线性辨识的故障检测

应用神经网络方法，提出了一种液体火箭发动机故障实时检测算法。神经网络采用非线性辨识技术贴近发动机的工作过程，并输出包合发动机故障信息的辨识误差信号。若辨识误差变大超过一定阈值，检测逻辑就预报发动机故障。在发动机启动阶段离线训练神经网络，在发动机稳态过程可以采用离线或在线学习算法。实验研究表明神经网络可以成功地应用于大型泵压式液体火箭发动机的故障检测。     

成分调整对DZ125合金凝固行为的影响

研究了标准成分的DZ125合金与以此为基础提高W、Al，降低Mo、Ti合金中的初生相的凝固顺序，确定了这两种合金在固-液范围内不同温度下的固-液相比例。结果表明，高W、Al低Mo、Ti合金显著缩小了合金凝固范围（Δ），使液相线温度提高了20℃，固相温度提高了70℃，并缩小失去技晶间毛细补缩能力时的温度与固相线之间的温度范围（ΔT2），从而减少了合金热裂倾向，提高了可铸性。Ti含量影响（γ＋γ'）共晶相尺寸、数量及形态，W、Wo对（γ＋γ'）共晶的数量、尺寸及形态均无影响。     

A Detection Algorithm for Optical Targets in Clutter

There is active interest in the development of algorithms for detecting weak stationary optical and IR targets in a heavy opticalclutter background. Often only poor detectability of low signal-to-noise ratio (SNR) targets is achieved when the direct correlation method is used. In many cases, this is partly obviated by using detection with correlated reference scenes [1, 2].This paper uses the experimentally justified assumption that most optical clutter can be modeled as a whitened Gaussian randomprocess with a rapidly space-varying mean and a more slowlyvarying covariance [2]. With this assumption, a new constant falsealarm rate (CFAR) detector is developed as an application of the classical generalized maximum likelihood ratio test of Neyman and Pearson. The final CFAR test is a dimensionless ratio. This test exhibits the desirable property that its probability of a false alarm(PFA) is independent of the covariance matrix of the actual noiseencountered. When the underlying noise processes are complex intime, similar considerations can yield a sidelobe canceler CFARdetection criterion for radar and communications. Performance analyses based on the probability of detection (PD)versus signal-to-noise ratio for several given fixed false alarm probabilities are presented. Finally these performance curves are validated by computer simulations of the detection process which use real image data with artificially implanted signals.     

Design and application of an Electric Tail Rotor Drive Control (ETRDC) for helicopters with performance tests

With the development of electric helicopters’ motor technology and the widespread use of electric drive rotors, more aircraft use electric rotors to provide thrust and directional control. For a helicopter tail rotor, the wake of the main rotor influences the tail rotor’s inflow and wake. In the procedure of controlling, crosswind will also cause changes to the tail disk load. This paper describes requirements and design principles of an electric motor drive and variable pitch tail rotor system. A particular spoke-type architecture of the motor is designed, and the performance of blades is analyzed by the CFD method. The demand for simplicity of moving parts and strict constraints on the weight of a helicopter makes the design of electrical and mechanical components challenging. Different solutions have been investigated to propose an effective alternative to the mechanical actuation system. A test platform is constructed which can collect the dynamic response of the thrust control. The enhancement of the response speed due to an individual motor speed control and variable-pitch system is validated.     

橇式起落架动刚度及阻尼特性试验研究

起落架动刚度及阻尼特性是研究直升机“地面共振”问题两个重要参数。刚进入国产化阶段的模式起落架迄今尚无可靠的理论计算方法来确定这两个参数．本试验研究利用某型直升机真实的模式起落架为试件，采用机械阻抗测量法来研究该起落架的动刚度及阻尼特性。试验使用电液伺服激振设备，对模式起落架进行不同频率的激振，实时测量相应的载荷及位移响应，从而得出了模式起落架的动刚度及阻尼。试验模拟了直升机完全停机及半升力卸载情况，在机场及冰面降落情况，以及３个不同方向的受载情况。试验结果已直接用于某型直升机的“地面共振”分析。