利用经验正交函数分解的大气密度模式校准方法

热层大气密度产生的阻力是作用在低轨航天器上最大的非引力摄动,现有大气密度模式存在15%~20%的偏差,难以满足空间任务应用需要。采用NRLMSISE-00模式作为密度参考标准,通过修正Jacchia-Roberts经验大气模式温度参数校准密度,建立温度修正量与密度的参数方程。针对部分区域修正量迭代计算发散问题,采用改进高斯牛顿迭代法求解方程。选择经验正交函数（EOF）分解方法分析修正量的时空特征,并与传统球谐（SH）分析的结果进行比较。结果表明,前4阶EOF基函数与前9项球谐基函数分别可提取温度修正量超过85%与80%的变化特征,EOF分解方法对温度修正量的表示效率高于球谐分析方法。第1阶EOF基函数反映了温度参数的整体偏差,第2~4阶EOF基函数对应的时间系数表明温度修正量的变化具有天周期性,且球谐分析得到的时间系数同样具有天周期性的特点。利用前4阶EOF基函数和前9项球谐基函数重构的温度修正量校准Jacchia-Roberts模式,校准后的模式密度偏差分别下降了9.06%与5.37%,表明EOF分解方法与传统球谐分析方法相比,能够更有效地修正温度参数,改进模式精度。     

地面燃气轮机单管燃烧室流量分配试验

对设计的100kW地面燃气轮机单管燃烧室空气流量分配进行了试验研究。在常压环境下采用堵孔法分别得到了旋流器、主燃孔和掺混孔的流量特性曲线,分析得到燃烧室不同结构的流量系数;试验研究了不同进口流量条件下燃烧室的流量分配,测量得到了燃烧室总压损失。研究发现:随着进口空气流量的增加,燃烧室的流量分配比例基本保持稳定,并且与燃烧室的设计空气比例基本吻合;随着燃烧室进口流量（雷诺数）的增加,旋流器、主燃孔和掺混孔的流量系数呈线性降低;随着进口流量（雷诺数）的增加,燃烧室总压损失逐渐增大;对主燃孔和掺混孔的流量特性测量中,两种测量方法得到的试验结果稍有差别,总体上看两种测量方法的试验结果较为接近。通过对比分析证明两种试验测量方法真实可靠,该研究结果可为100kW地面燃气轮机燃烧室的设计与优化提供依据。      

浅谈波音737NG飞机APU滑油系统一项监控指标在故障监控中的应用

波音737NG飞机APU故障影响航班运行,而APU滑油系统是其安全运行的重要保障,大多数APU的故障都能够从滑油系统的监控指标中找到故障征兆。本文基于737NG飞机APU滑油系统工作原理,提出了一项APU滑油系统的监控指标——温升速率,并利用该指标总结排故方法进行重点故障的监控,有效地提高了排故效率。     

考虑喷油润滑的附件机匣温度场分析

附件机匣作为航空发动机重要部件之一,其产热和散热的问题比较复杂.针对以往附件机匣相关研究只关注固体域的产热、散热分析,而对滑油散热作用不能充分考虑这一问题的现状,提出了基于流体仿真思想的稳态温度场分析方法.首先,通过分析附件机匣产热、散热问题的基本规律和特点,进一步采用k-ε湍流模型来模拟机匣内的情况,多相流模型模拟滑油,并且使用多参考坐标系模拟滑油在运动过程中的换热.最后,以某附件机匣作为具体应用案例,验证了方法的正确性和可行性,从而形成了一套行之有效的使用FLUENT软件对附件机匣进行稳态温度场仿真分析的模型和方法.研究的成果对于后续附件机匣的可靠性与寿命分析有重要支撑作用.      

中点箝位型光伏并网逆变器调制策略及效率对比

传统三电平中点箝位(Three-level neutral point clamped,3L-NPC)半桥逆变器在高压大功率条件下,由于开关器件损耗不均衡而使其容量受限,因此衍生了多种NPC型三电平半桥拓扑。为了优化选取NPC型拓扑及调制策略,对4种3L-NPC型拓扑(二极管NPC、有源式NPC、层叠式NPC及有源层叠式NPC)的调制策略及开关器件损耗分布进行了对比分析,并研制了一台5kW的NPC型统一实验平台,进行了效率测试。理论分析与实验结果表明:(1)根据零电平续流路径的配置不同,NPC型拓扑主要有4种调制策略;(2)选取合理的NPC型拓扑及调制策略,不仅可以均衡器件损耗,而且系统效率基本不变,为逆变器的扩容奠定了基础。     

Experimental study of a flush wall scramjet combustor equipped with strut/wall fuel injection

In this study a flush wall scramjet combustor is tested in a supersonic incoming air flow with the Mach number of 3 which is generated by an air vitiation heater producing the stagnation temperature of 1505 K. Using liquid kerosene as the fuel, the flame is stabilized by means of a centrally mounted O₂ pilot strut after being ignited by a plasma torch. During experimental measurements, the fuel is injected with a constant equivalence ratio of 0.8 according to specified strut/wall injection ratios, i.e., a portion of the fuel amount is injected from the strut while the rest is injected from the wall. The strut and wall injectors are arranged at the same axial position. The combustion performance and wall temperature gradients are evaluated with various fuel feeding ratios between the wall and the strut. Experimental results show, when the equivalence ratio is constant and the axial injection position is fixed, the combustion characteristics vary significantly with the strut/wall fuel feeding ratio, especially when this ratio is close to its lowest and highest limits. Among the four fuel feeding ratios examined, the strut only injection mode and the average distributed strut/wall injection mode show the best combustion performance. However, the strut/wall injection mode produces a smaller wall temperature gradient compared to the strut only injection mode, which is due to the significant film cooling effect caused by the wall injected liquid kerosene.     

Influence of lunar topography on simulated surface temperature

The surface temperature of the Moon is one of the essential parameters for the lunar exploration, especially to evaluate the Moon thermophysical features. The distribution of the temperature is heavily influenced by the Moon topography, which, however, is rarely studied in the state-of-art surface temperature models. Therefore, this paper takes the Moon topography into account to improve the surface temperature model, Racca model. The main parameters, such as slopes along the longitude and latitude directions, are estimated with the topography data from Chang’E-1 satellite and the Horn algorithm. Then the effective solar illumination model is then constructed with the slopes and the relative position to the subsolar point. Finally, the temperature distribution over the Moon surface is obtained with the effective illumination model and the improved Racca model. The results indicate that the distribution of the temperature is very sensitive to the fluctuation of the Moon surface. The change of the surface temperature is up to 150 K in some places compared to the result without considering the topography. In addition, the variation of the surface temperature increases with the distance from the subsolar point and the elevation, along both latitude and longitude directions. Furthermore, the simulated surface temperature coincides well with the brightness temperature in 37 GHz observed by the microwave sounder onboard Chang’E-2 satellite. The corresponded emissivity map not only eliminates the influence of the topography, but also hints the inherent properties of the lunar regolith just below the surface. Last but not the least, the distribution of the permanently shadowed regions (PSRs) in the lunar pole area is also evaluated with the simulated surface temperature result.     

载人航天器AIT中心微生物分布特征分析

为更好地控制载人航天器中的微生物水平,指导未来航天器研制中微生物控制设计,文章采用撞击法对3个载人航天器AIT中心的空气菌落数量和菌种分布特征进行了分析。厂房菌落数比较结果显示:北京AIT中心的细菌水平显著高于其他地区AIT （P<0.05）,天津AIT中心的真菌水平显著高于其他地区AIT （P<0.05）,酒泉AIT中心的总菌数在3个地区中最少（P<0.05）。厂房菌种类别比较结果显示:北京AIT中心的优势细菌为微球菌属、葡萄球菌属等,优势真菌为白假丝酵母菌;天津AIT中心的优势细菌为芽胞杆菌属,优势真菌为曲霉属和青霉属等;酒泉AIT中心的优势细菌为芽胞杆菌属、葡萄球菌属等,优势真菌为曲霉属和球毛壳霉等。本研究表明:各AIT中心的空气微生物分布具有明显的地区差异,这不仅与不同AIT中心所在地的气候特征和厂房设计有关,还受到人员管理因素的影响。文章最后为我国空间站AIT中心的微生物控制设计提出了一些建议。     

Small amplitude ion acoustic solitons in a weakly magnetized plasma with anisotropic ion pressure and kappa distributed electrons

The Zakharov–Kuznetzov (ZK) equation is derived for nonlinear electrostatic waves in a weakly magnetized plasma in the presence of anisotropic ion pressure and superthermal electrons. The anisotropic ion pressure is defined using Chew–Goldberger–Low (CGL) while a generalized Lorentzian (kappa) distribution is assumed for the non-thermal electrons. The standard reductive perturbation method (RPM) is employed to derive the two dimensional ZK equation for the dynamics of obliquely propagating low frequency ion acoustic wave. The influence of spectral index (kappa) of non-thermal electron on the soliton is discussed in the presence of anisotropic ion pressure in plasmas. It is found that ion pressure anisotropy and superthermality of electrons affect both the width and amplitude of the solitary waves. On the other hand the magnetic field is found to alter the dispersive property of the plasma only, and hence the width of the solitons is affected while the amplitude of the solitary waves is independent of external magnetic field. The numerical results are also presented for illustrations.     

多退化变量下基于Copula函数的陀螺仪剩余寿命预测方法

针对惯性导航系统中陀螺仪多退化变量条件下的剩余寿命（RUL）预测问题,提出了一种基于Copula函数的多退化变量剩余寿命预测方法。首先,针对退化变量间不同的退化轨迹,采用不同的方法进行退化建模,并对于陀螺漂移系数样本标准差数据波动性随时间递增的特性,提出了一种方差时变的正态随机过程退化建模方法,得到了陀螺仪剩余寿命的边缘分布函数。然后,通过Copula函数来描述退化变量之间的相关性,将得到的剩余寿命的边缘分布进行融合,得到了陀螺仪剩余寿命的联合分布函数。最后,通过陀螺仪实例分析验证了方法的适用性和可行性。