平面遮挡分析法及其在航天器气动力矩分析中的应用

针对空间站等复杂构型航天器迎流面积和气动力矩的快速分析问题,提出一种平面遮挡分析法。该方法在与迎流垂直的方向上,选定一个二维投影平面进行航天器组成单元的划分和二维外形信息的定义;通过标志符、差值函数及相关的单元外形边界搜索规则定义和操作,实现迎流面积和遮挡面积的计算。平面遮挡分析法减少了遮挡分析所需使用的航天器外形信息维度,可以提高遮挡分析的效率。然后给出基于该平面遮挡分析法对迎流面积和压心位置进行计算的数学模型,对使用的气动力矩分析模型进行说明。以一个非对称构型的空间站为例,对相应的迎流面积和气动力矩进行仿真计算和对比验证。结果表明,平面遮挡分析法具有较为明显的计算时间优势,同时具备较高的计算精度。     

两轮升压式空气动压轴承涡轮冷却器起浮压力计算

通过分析两轮升压式空气动压轴承涡轮冷却器的起浮原理,建立了计算起浮压力的方法.按照该方法编制程序计算了某型涡轮冷却器在不同条件下的起浮压力,计算结果与试验实测数据吻合较好,说明计算方法具有较高准确度.通过计算和分析可以看到涡轮出口背压和轴承预紧对轴承起浮影响较大,背压越低则起浮压力越低;轴承预紧力越大则起浮压力越高.      

螺纹结构力矩及其衰退机理分析

阐述了得出螺栓拧紧力矩的方法,结合预紧力和预紧力矩之间的关系,给出其理论方程和实验方程,分析了预紧力、螺纹摩擦转矩和螺母支承面摩擦转矩三者的分配情况。以此为基础,从结构变形与应力释放、材料表面摩擦力变化等方面对力矩衰退的原因进行了初步分析,并提出设定拧紧力矩安全系数和定期校核拧紧的措施,供螺纹结构设计及其使用维护参考。     

滚动轴承摩擦力矩的乏信息模糊预报

滚动轴承摩擦力矩的波动具有不确定性,属于概率分布与趋势规律都未知的乏信息系统.这阻碍了对轴承摩擦力矩的小样本分析与总体把握.为此,以模糊集合理论为基础,从小样本入手,建立了航天轴承摩擦力矩参数的经验概率密度函数及其模糊预报模型,并对摩擦力矩的均值上界和最大值上界进行预报.对HKTA和HKTB两种轴承摩擦力矩参数的试验研究表明,在99%～100%置信水平下,预报结果与试验结果之间的误差很小,最大绝对误差仅为0.081 1个设定单位,最大相对误差仅为10.165%,可以满足航天工程的要求.      

Impact of the orbital eccentricity on the attitude performance before and after the deorbiting phase for Alsat-1

Due to the presence of periodic forcing terms in the gravity gradient torque, orbit eccentricity may produce large response for the roll, yaw and pitch angles. This paper investigates the influence of the orbit eccentricity on the performance of the attitude determination and control subsystem (ADCS) pointing of passive Low Earth Orbit (LEO) satellites stabilized by a gravity gradient boom or having long appendages before and after the deorbiting operation. The contribution of this work is twofold. First, the satellite attitude dynamics and kinematics are modeled by introducing the orbit eccentricity in the equations of motion of a LEO satellite in order to provide the best scenario in which satellite operators can keep the nominal functionality of LEO satellites with a gravity gradient boom after the deorbiting operation. Second, a Quaternion-based Extended Kalman Filter (EKF) is analyzed when the orbit eccentricity is considered in order to determine the influence of this disturbance on the convergence and stability of the filter. The simulations in this work are based on the true parameters of Alsat-1 which is a typical LEO satellite stabilized by a gravity gradient boom. The results show that the orbit eccentricity has a big influence on the pointing system accuracy causing micro-vibrations that affect the geocentric pointing particularly after the deorbiting phase. In this case, satellites have no orbital correction option. The Quaternion-based Extended Kalman Filter analyzed in this paper, achieved satisfactory results for eccentricity values less than 0.4 with respect to pointing system accuracy. However, singularities were observed for eccentricity values greater than 0.4.     

改进的参考电压矢量获取方法

针对基于空间矢量调制的永磁同步电机直接转矩控制方法中,参考电压矢量获取涉及电机参数,而电机参数的变化又导致预测结果不可靠的问题,提出了一种不依赖电机参数的参考电压矢量获取方法。通过对转矩误差以及定子磁链幅值误差进行PI控制,对其输出量分别分配一定的权重,用其绝对值的加权,作为参考电压矢量幅值的控制量,用其比值作为确定参考电压矢量相对于定子磁链矢量角度偏差的依据。仿真结果表明,该方法能很好克服电机参数变化造成的影响,从而试验验证了该方法的有效性。     

An estimation of Envisat’s rotational state accounting for the precession of its rotational axis caused by gravity-gradient torque

The rotational state of Envisat is re-estimated using the specular glint times in optical observation data obtained from 2013 to 2015. The model is simplified to a uniaxial symmetric model with the first order variation of its angular momentum subject to a gravity-gradient torque causing precession around the normal of the orbital plane. The sense of Envisat’s rotation can be derived from observational data, and is found to be opposite to the sense of its orbital motion. The rotational period is estimated to be $(120.674\pm 0.068)·\exp \left((4.5095\pm 0.0096)\times {10}^{-4}·t\right)\text{s}$, where t is measured in days from the beginning of 2013. The standard deviation is 0.760?s, making this the best fit obtained for Envisat in the literature to date. The results demonstrate that the angle between the angular momentum vector and the negative normal of the orbital plane librates around a mean value of $8.53°\pm 0.42°$ with an amplitude from about $0.7°$ (in 2013) to $0.5°$ (in 2015), with the libration period equal to the precession period of the angular momentum, from about 4.8?days (in 2013) to 3.4?days (in 2015). The ratio of the minimum to maximum principal moments of inertia is estimated to be $0.0818\pm 0.0011$, and the initial longitude of the angular momentum in the orbital coordinate system is $40.5°\pm 9.3°$. The direction of the rotation axis derived from our results at September 23, 2013, UTC 20:57 is similar to the results obtained from satellite laser ranging data but about $20°$ closer to the negative normal of the orbital plane.     

基于直接转矩控制电励磁同步电机转子励磁电流控制策略

同步电机转子励磁电流控制方式直接影响电机的运行特性。针对直接转矩控制电励磁同步电机提出一种全速度范围内转子励磁电流优化控制策略,它直接利用转矩给定和定子磁链给定计算出转子励磁电流给定值。仿真和实验结果表明:额定转速以下转子励磁电流较小,降低了转子绕组的发热;额定转速以上转子励磁电流较大,提高了电机负载能力;恒转矩区和恒功率区之间转换不需要设定过渡区,过渡平滑;全速度范围内电机的外功率因数均近似等于1。     

用空间电压矢量调制异步电动机的直接转矩控制

为了减小基本直接转矩控制(Basic-DTC)的转矩和磁链脉动,采用空间电压矢量调制(SVM)与直接转矩控制相结合(SVM-DTC)的方法。从直接转矩控制的基本原理出发,引入SVM方法,详细给出了一种改进型基于磁链矢量偏差法的异步电动机SVM-DTC的分析与实现过程,同时给出了修正的应用于SVM-DTC的磁链观测方法。仿真研究表明,与Basic-DTC方法相比,该方法除了能使转矩和磁链脉动大为减小外,还具有与传统直接转矩控制一样好的动态性能。最后,给出了SVM-DTC与Basic-DTC的实验对比结果,证明了该方法的有效性。     

电力作动系统容错电机拓扑结构与控制策略

容错电机以其可靠性高、容错能力强以及恶劣环境工作能力强等优点得到了国内外电机领域广泛关注,其工作原理、拓扑结构、电磁性能和控制策略等已有广泛而深入的研究,研究结果表明该类电机非常适合应用于全电/多电飞机电力作动系统.本文从拓扑结构和控制算法两大方面对电力作动系统用容错电机的关键技术进行分析和总结.在拓扑结构方面,横向比...