基于闭环电流平均值法的永磁同步电机谐波抑制方法

由于逆变器的非线性及永磁同步电机(PMSM)的气隙磁场畸变,在运行过程中PMSM定子电流中含有大量的谐波分量,导致电流波形发生畸变,从而引起较大的转矩脉动。针对传统谐波抑制方法采用低通滤波器(LPF)提取5、7次谐波分量,动态响应时间长,稳态误差大的问题,提出了闭环电流平均值法提取谐波分量。仿真结果表明,闭环电流平均值法可以提高系统的快速性和稳定性。将电流平均值法应用于PMSM谐波抑制系统,仿真结果表明:基于闭环电流平均值法的谐波电压注入法可以降低电流波形的畸变率及5、7次谐波含量。     

一种混合励磁同步发电机的气隙磁密分析及其电压谐波抑制

为改善混合励磁同步发电机的气隙磁密分布,采用三段式气隙长度对转子进行了优化,对比了优化前后的气隙磁密。为抑制电压谐波,在完成转子结构优化的基础上,进一步采用短距、分布电枢绕组以及定子斜槽等措施。最后对样机电压波形进行了实测和质量分析,结果表明:采用三段式气隙长度与定子斜槽相结合,可将电压波形的总谐波失真(THD)抑制在5%的范围内。此外,探讨了偏心距法在切向/径向混合励磁电机中应用的可行性,并对比了分别采用偏心距法和三段式气隙长度法时的气隙磁密。     

电大尺寸天线罩电磁特性高效数值仿真技术

针对电大尺寸天线罩电磁特性，分析研究了快速求解表面积分方程的多层快速多极子算法及其改进技术。构造了具有良好矩阵性态的积分方程形式，提出加速迭代求解的并行预条件技术，利用分组稀疏化方式构造预条件矩阵，显著降低了迭代求解次数。采用快速球谐展开技术对聚合和配置因子项进行压缩，将其存储量降低了2/3。通过数值算例验证了方法的精确性和高效性，并实现了大型带罩阵列天线辐射特性的仿真分析。     

Characterization of the low latitude plasma density irregularities observed using C/NOFS and SCINDA data

Complex electrodynamic processes over the low latitude region often result in post sunset plasma density irregularities which degrade satellite communication and navigation. In order to forecast the density irregularities, their occurrence time, duration and location need to be quantified. Data from the Communication/Navigation Outage Forecasting System (C/NOFS) satellite was used to characterize the low latitude ion density irregularities from 2011 to 2013. This was supported by ground based data from the SCIntillation Network Decision Aid (SCINDA) receivers at Makerere (Geographic coordinate 32.6°E, 0.3°N, and dip latitude ?9.3°N) and Nairobi (Geographic coordinate 36.8°E, ?1.3°N, and dip latitude ?10.8°N). The results show that irregularities in ion density have a daily pattern with peaks from 20:00 to 24:00 Local Time (LT). Scintillation activity at L band and VHF over East Africa peaked in 2011 and 2012 from 20:00 to 24:00 LT, though in many cases scintillation at VHF persisted longer than that at L band. A longitudinal pattern in ion density irregularity occurrence was observed with peaks over 135–180°E and 270–300°E. The likelihood of ion density irregularity occurrence decreased with increasing altitude. Analysis of C/NOFS zonal ion drift velocities showed that the largest nighttime and daytime drifts were in 270–300°E and 300–330°E longitude regions respectively. Zonal irregularity drift velocities over East Africa were for the first time estimated from L-band scintillation indices. The results show that the velocity of plasma density irregularities in 2011 and 2012 varied daily, and hourly in the range of 50–150 m s^?1. The zonal drift velocity estimates from the L-band scintillation indices had good positive correlation with the zonal drift velocities derived from VHF receivers by the spaced receiver technique.     

高阶带谐摄动下卫星相对运动精确动力学模型

在考虑J 2 项摄动的卫星相对运动精确动力学模型基础上,推导了可以精确到任意阶带谐非球形引力摄动的卫星相对运动精确动力学模型,还给出了一组简洁的基于参考卫星轨道要素（Reference Satellite Variables）的微分方程,能够描述精确到任意阶带谐非球形引力的卫星地球轨道运动。由于在模型推导过程中没有引入任何简化,新推导的结果适用于任意偏心率的地球轨道。     

Gravity modeling in aerospace applications

The science of inertial navigation has evolved to the point that the traditional gravity model is a principal error source in advanced, precise systems. Specifically, the unmodeled vertical deflections of the earth's gravitational field are a major contributor to CEP (circular error probable) divergence in precise terrestrial inertial navigation systems (INS). Over the years, several studies have been undertaken to the development of advanced techniques for accurate, real-time compensation of gravity disturbance vectors. More complex on-board gravity models which compute vertical deflection components will reduce the CEP divergence rate, but imperfect modeling due to on-board processing limitations will still cause residual vertical deflection errors. In order to eliminate or reduce gravity-induced errors in the INS requires measurement of gravity disturbance values and in-flight compensation to the inertial navigator. It is assumed in this paper that gravity disturbance values have been measured prior to the airborne mission and various techniques for compensation are to be considered. As part of a screening process in this study, several gravity compensation techniques (both deterministic and stochastic models) were investigated. The screening process involved identification of gravity models and algorithms, and developments of selection criteria for subsequent screening of the candidates.     

昆明上空电离层D区电子密度季节变化的首次观测分析

通过分析2008年8月至2009年7月昆明站(25.6°N, 103.8°E) 中频(MF)雷达观测数据, 研究了太阳活动低年电离层D区电子密度的季节变化特性,发现D区电子密度主要呈现半年变化特征, 即在春秋季电子密度较大, 而在夏冬季则较小, 这与国际参考电离层(IRI)预测的年变化趋势不一致, 但与昆明站电离层测高仪的最低回波频率f_min的观测结果相符. 同时比较了D区电子密度半年变化与纬向风半年变化的关系, 发现二者之间保持了非常一致的变化趋势并对这种一致性的内在原因进行了分析.      

A Simulation of the Mid-and Low-latitude Ionospheric Electric Fields

A theoretical model of ionospheric electric fields at mid- and low-latitudes is developed. In the geomagnetic dipolar coordinate system, the ionospheric dynamo equations were solved, and the ionospheric electric potential and electric field were derived respectively. Major parameters for the model inputs, such as the neutral winds, the densities and temperatures of electron, ions and neutrals, are obtained from empirical models. The global ionospheric electrical potential and field at mid- and low-latitudes derived from our model are largely in agreement with the results presented by other authors and the empirical model. Using our model, it is found that the diurnal component of the HWM93 wind mainly contributed to the formation of the vertical electric field, while the semidiurnal component mainly contributed to the zonal electric field. Finally, by adjustment of the input F region winds and conductivities, most discrepancies between our model and the empirical one can be eliminated, and it is proved that the F region dynamo is the most significant contribution to the electric fields.      

GTCP131-9A辅助动力装置性能参数换算公式研究

对GTCP131-9A辅助动力装置（APU）性能参数（排气温度和燃油流量）换算公式展开研究。提出了一种研究燃气轮机相似性的通用方法。采用这种方法得出了构成该单转子定轴燃气轮机相似的充分条件是需要有3个相互独立的相似准则数相等,这3个相似准则数可以是飞行马赫数、折合转速、折合功率,其他相似参数是这3个相似准则数的函数。根据该发动机相似性,采用小偏差法,给出了试车过程中存在的排气附加阻力、燃油热值偏差和功率偏差的性能参数的小偏差修正方程。结果表明:在输出功率和大气压力比值为定值的条件下,GTCP131-9A辅助动力装置性能参数换算公式是进气总温多项式与排气附加阻力修正项、燃油热值变化修正项、功率变化修正项之和。