多段翼型前缘缝翼吹气流动与噪声控制数值研究

根据吹气边界层流动控制的特点,探索了前缘缝翼流动控制和减噪技术。利用FLUENT软件对某多段翼型进行数值模拟,求解RANS方程和FW-H声学方程。在前缘缝翼下翼面设置吹气孔,通过改变吹气系数,研究缝翼缝道内吹气流动控制对二维多段翼型气动性能及噪声特性的影响。计算结果表明:应用缝翼吹气技术可在相同迎角下获得更高的升力系数,且能减小缝翼缝道内的分离,降低角涡引起的噪声;不同吹气系数对多段翼升力和噪声有不同程度的影响;迎角为6毅时,吹气控制可以使低频噪声减少2~4.5dB。     

整流罩用降噪材料与结构及声场分析方法

为了有效改善整流罩内声振环境,最常见并且高效的方法是通过在整流罩的壁面铺覆降噪材料来降低噪声的声压级。本文总结了国内外整流罩降噪材料的工程应用及研究进展,详细介绍了几种主要降噪材料的基本性能和降噪原理,对不同频段下适用的声场分析方法及过程作了阐述,并提出了对我国在降噪材料领域研究发展的建议。     

光栅莫尔条纹信号细分方法设计与Simulink仿真CSCD

根据计量光栅莫尔条纹信号高精度细分的要求,提出了一种基于ADC幅值采样和相位解算的光栅细分方法,并利用Simulink搭建仿真模型,使两路正余弦信号通过正余切变换、幅值采样、固定相位步长细分等处理后输出为两路正交编码信号。仿真实验表明,该细分方法在输入理想信号情况下细分倍数主要与ADC采样精度有关,提高ADC采样位数可有效提高最大细分倍数。通过在两路时变sin/cos信号中添加幅值不等、相位不正交以及高次谐波分量等干扰噪声的仿真实验,验证了该方法的细分精度与信号质量有关。     

原子磁强计原子气室无磁加热温控系统设计

介绍一种用于原子磁强计原子气室的无磁加热温控系统设计。针对温控系统加热电流产生的磁场干扰，设计了双层加热丝加热膜结构的加热器件，该加热器件利用同层平行反向电流和层间平行反向电流产生的磁场相互抵消以减小加热电流磁场噪声；设计了滑动平均滤波器对采集的温度信号实施滤波以减小随机噪声的干扰；结合设计的高频加热信号的产生电路、幅度控制电路和功率放大电路开展了实验测试。测试结果表明，研制的双层加热丝加热膜结构加热器件相比单层加热丝加热膜结构加热器件的电流磁场噪声抑制能力提高了约16倍，实现的无磁加热温控系统的温控能力达到1.2‰。     

Efficient prediction of ground noise from helicopters and parametric studies based on acoustic mapping

Based on the acoustic mapping, a prediction model for the ground noise radiated from an in-flight helicopter is established. For the enhancement of calculation efficiency, a high-efficiency second-level acoustic radiation model capable of taking the influence of atmosphere absorption on noise into account is first developed by the combination of the point-source idea and the rotor noise radiation characteristics. The comparison between the present model and the direct computation method of noise is done and the high efficiency of the model is validated. Rotor free-wake analysis method and Ffowcs Williams-Hawkings (FW-H) equation are applied to the aerodynamics and noise prediction in the present model. Secondly, a database of noise spheres with the characteristic parameters of advance ratio and tip-path-plane angle is established by the helicopter trim model together with a parametric modeling approach. Furthermore, based on acoustic mapping, a method of rapid simulation for the ground noise radiated from an in-flight helicopter is developed. The noise footprint for AH-1 rotor is then calculated and the influence of some parameters including advance ratio and flight path angle on ground noise is deeply analyzed using the developed model. The results suggest that with the increase of advance ratio and flight path angle, the peak noise levels on the ground first increase and then decrease, in the meantime, the maximum Sound Exposure Level (SEL) noise on the ground shifts toward the advancing side of rotor. Besides, through the analysis of the effects of longitudinal forces on miss-distance and rotor Blade-Vortex Interaction (BVI) noise in descent flight, some meaningful results for reducing the BVI noise on the ground are obtained.     

On the application of Exploratory Data Analysis for characterization of space weather data sets

This paper presents an overview of the mathematical foundations for techniques in Exploratory Data Analysis (EDA) for the purpose of investigating the relationships among the numerous variables in large sets of multivariate space weather data. Specifically, we cover techniques in Principal Components Analysis (PCA) and Common Factor Analysis (CFA). These techniques are illustrated using space weather activity indices collected during the year 2002 and the corresponding noon-time hmF2 data from the International Reference Ionosphere (IRI). A CFA is used to categorize the activity indices, and a PCA is used to derive two macro-indices of activity to ascertain the strength of solar and geomagnetic activity. These macro-indices are then used to compare and contrast IRI’s noon-time hmF2 values at six different geographic stations. It was found that the correlation between hmF2 and the macro-indices more accurately represented the variation of this correlation with latitude found in previous studies than if we used an isolated conventional index, such as SSN and AE. We also found that the daily maximum value of the Polar Cap Index was dependent on both solar and geomagnetic activity, but the closely-related cross-Polar Cap Potential was solely associated with elevated levels of geomagnetic activity, which is a unique result compared to previous studies. We argue that the discrepancy can be explained by the difference in experiment designs between the two studies. This paper demonstrates the usefulness of EDA in space weather studies of large multivariate data sets.     

跟踪微分器在GLONASS定位数据处理中的应用研究

本文介绍了GLONASS定位系统,给出了跟踪微分器的滤波特性。将跟踪微分器用于GLONASS定位数据处理。进行了误差分析及仿真研究。结果表明,这种方法可显著提高GLONASS定位精度,减小定位误差,具有一定的优越性。     

民用飞机发动机监测方法研究

对民用飞机发动机状态监测和故障诊断方法进行了研究,提出了一种能够实时反映零件故障信息的油液在线静电监测方法,设计并搭建了一套静电监测系统及实验平台,开展了循环润滑条件下销盘滑动摩擦磨损实验,使用自制的油液静电传感器对油路中磨粒进行监测。实验结果表明油液静电传感器能够监测到金属材料荷电颗粒,感应电压幅值与磨粒大小具有相关性,感应电压波形与磨粒荷电特性有关,验证了静电传感器在线监测的有效性,为判断故障提供了进一步的依据。     

民用飞机增升装置气动噪声学风洞试验初步研究

采用模拟退火法阵列优化设计技术设计了对数螺旋麦克风阵列,开发了基于“波束成型理论冶的阵列试验数据处理软件。将风洞麦克风相阵列噪声识别技术用于SCCH模型增升装置气动噪声研究,开展了增升装置气动噪声源的远场定位探测和强度测量,并用数据处理软件对风洞试验数据进行处理。试验结果表明,随着观察频率的变化缝翼噪声声源的位置与强度会发生变化,襟翼侧缘噪声是一个宽频噪声,不同频率下其强度分布存在差异。同时也发现缝翼安装支架对缝翼和襟翼气动噪声声源有较大影响。文中也给出了多种工况下缝翼和襟翼噪声源分布。     

消除CMOS管内部噪声的方法

介绍了一种通过改进电路结构来消除CMOS管内部的噪声，最终达到降低总输出噪声的技术。首先从理论上证明了这种技术的原理，然后把这种技术应用到具体的低噪声放大器电路中，通过PSPICE软件模拟仿真，比较和分析了采用这种技术前后LNA电路的总输出噪声、输出信噪比和电压增益。