动态无线能量传输系统参数化设计与优化

无线能量传输技术以其操作方便快捷、适应快速更换及维修、减少机动作业无缆影响、可快速扩展、大幅减小设备电池质量、无触电危险、极限环境适应性强等特点被广泛应用于各领域。针对给定输入和约束,要求对动态无线能量传输系统的耦合机构尺寸和电路参数进行充分优化设计以满足一定输出功率效率的需求。经过前期对电路和耦合机构磁路的理论及仿真研究,得到了系统各参数变化时将导致系统输出特性随之如何变化的理论依据。基于此,建立了动态无线能量传输系统的参数化设计模型,并进行优化设计流程及步骤,以最简化的计算流程和最少的工作量,实现了动态无线能量传输系统的发射轨道和电路的参数化设计。该研究将对动态无线能量传输系统的多目标多参数化自动最优化设计具有重要的指导意义。     

Modeling and analysis of solar Doppler difference bias with arbitrary rotation axis

The solar rotation causes the solar Doppler difference bias, which leads to the decline of the velocity measurement accuracy. Modeling and compensation are an effective solution. The limited model with specific geometric direction, where the solar rotation axis is perpendicular to the plane through the Sun, the Earth and Mars, was established. However, in fact, the geometric relationship among the Sun, Mars and the spacecraft is not fully in line with the hypothesis of the model due to the spacecraft orbital angle and the solar rotation axis drift. Thus, this model is not consistent with the fact. In order to solve this problem, a universal solar Doppler difference bias model, which provides the expression with arbitrary rotation axis, is established in this paper. In this method, for any point at the solar surface, four variables including the direction of the solar rotation linear velocity at this point, the distance from this point to the rotation axis, the vector from this point to Mars, and the vector from this point to the spacecraft are calculated. Based on these four variables, the solar Doppler difference bias corresponding to this point is obtained. The theoretical analysis and simulation results demonstrate that the solar Doppler difference bias model with the actual rotation axis is different from that with one of the specific rotation axes. Therefore, it is indispensable to build the proposed model for compensation. Besides, the direction of the solar rotation axis, the spacecraft-Mars-Sun angle and the spacecraft-to-Mars distance are important impact factors for the proposed model.     

The low and middle latitude semi-annual anomaly in NmF2 near noon: A statistical study

Hourly values of the F2-layer peak density, NmF2, measured by 99 ionosonde stations near noon from 1957 to 2010 at low and middle geomagnetic latitudes of the northern and southern geographic hemispheres are used in a statistical study of the F2-region semi-annual anomaly. The equinox/winter and equinox/summer geomagnetically quiet NmF2 ratios, X and Y, taken near noon over each ionosonde for approximately the same winter, equinox, and summer solar activity conditions are analyzed. The conditional probabilities of occurrences of X and Y in intervals of X and Y, the most frequent values of X and Y, the mean expected values of X and Y, and the conditional probability to observe the F2-region semi-annual anomaly are calculated and studied for the fist time for low, moderate, and high solar activity conditions. These statistical parameters are averaged over 5° geomagnetic latitude interval in the northern and southern geographic hemispheres, and the trends in these averaged statistical characteristics of the NmF2 semi-annual anomaly are calculated and studied for the fist time. It is shown that the median approach can produce the incorrect conclusions about the absence of the NmF2 semi-annual anomaly.     

Equatorial vertical E × B drift velocities inferred from ionosonde measurements over Ouagadougou and the IRI-2007 vertical ion drift model

F-region vertical plasma drift velocities were deduced from the hourly hmF2 values acquired from ionogram data over a near dip equatorial station Ouagadougou (12.4°N, 358.5°E, dip angle 5.9°N) in Africa. Our results are compared against the global empirical model of Scherliess and Fejer (1999) incorporated in the IRI model (IRI-2007) for 1600 to 0800 LT from 1 year of data during sunspot maximum year of 1989 (yearly average solar flux intensity, F10.7 = 192) corresponding to the peak phase of solar cycle 22, under magnetically quiet conditions. The drifts are entirely downward between 2000 and 0500 LT bin for both techniques and the root mean square error (RMSE) between the modeled and the ionosonde vertical plasma drifts during these periods is 3.80, 4.37, and 4.74 m/s for June solstice, December solstice and equinox, respectively. Ouagadougou average vertical drifts show evening prereversal enhancement (PRE) velocity peaks (V_ZP) of about 16, 14, and 17 m/s in June solstice, December solstice, and equinox, respectively, at 1900–2000 LT; whereas global empirical model average drifts indicate V_ZP of approximately 33 m/s (June solstice), 29 m/s (December solstice), and 50 m/s (equinox) at 1800 LT. We find very weak and positive correlation (+0.10376) between modeled V_ZP versus F10.7, while ionosonde V_ZP against F10.7 gives worst and opposite correlation (−0.05799). The results also show that modeled V_ZP–Ap indicates good and positive correlation (+0.64289), but ionosonde V_ZP–Ap exhibits poor and negative correlation (−0.22477).     

民用飞机后机身参数化设计探究

通过对民用飞机后机身外形特征的分析,总结了民机后机身外形定义的关键参数,研究后机身外形参数化外形成型的可能性,提出了民机外形参数化设计的方法和思路。     

基于改进粒子群算法的航空发动机状态变量建模

为了克服现有航空发动机状态变量建模过程中的不足,采用了一种改进粒子群算法建立航空发动机状态变量模型。首先改进了粒子群算法,提出一种每个粒子根据自身适应值动态调整其惯性系数方法来平衡搜索性能;对群体最优位置进行实时的代内更新以提高搜索速度;为避免陷入局部最优,在最优个体附近进行随机搜索。其次利用该算法建立航空发动机状态变量模型,根据航空发动机在稳态点处的线性化模型应与在该同一稳态工作点处的非线性模型响应一致的原则构造适应值函数,仿真结果表明所建立的状态变量模型不论是稳态过程还是动态过程都与非线性模型响应基本一致,建模精度较高,建立过程简便。     

基于螺旋理论的航天器姿轨耦合分析

针对航天器运动姿轨耦合性问题,对基于螺旋理论得到的航天器运动模型,定性地分析了姿轨耦合特性。采用参数分析法,从模型所包含的耦合项出发,逐次改变各个参数,进而推导出对应的耦合表达式。为了检验耦合性对控制效果的影响,设计了PD 控制律并进行数值仿真。理论分析和仿真结果进一步证明,基于螺旋理论的航天器姿轨模型,其姿态和轨道运动之间是相互影响的,从控制角度而言,姿态运动对轨道运动影响相对更为严重,容易出现了大的振荡,而轨道运动对姿态运动的影响基本可以忽略,为工程实践提供参考。     

基于数据挖掘技术的金融信用决策管理系统

论文首先介绍了数据挖掘的概念及相关技术,然后论述了数据挖掘技术在金融信用决策管理系统中的应用,通过对预测解析、内在理解、决策建模、策略优化和策略精调的介绍,对数据挖掘的实现进行了有效描述.     

基于微观结构的航空铝合金点蚀扩展行为研究

点蚀是航空铝合金材料在服役环境下常见的损伤形式,在疲劳载荷作用下容易形成裂纹,缩短结构的疲劳寿命。为了深入研究点蚀对航空铝合金结构腐蚀疲劳寿命的影响,基于铝合金电化学腐蚀机理和铝合金微观结构,以点蚀蚀坑尺寸为研究参量,对航空铝合金点蚀扩展行为进行建模研究,并将模型计算结果与LY12CZ铝合金点蚀试验结果进行对比分析。结果表明:所构建的铝合金点蚀扩展模型较为合理地反映了铝合金点蚀蚀坑尺寸参数的变化规律。