叠层荧光集光太阳能光伏器件的性能模拟和优化

荧光集光太阳能光伏器件可以减少太阳能电池的用量,有效降低光伏发电的成本.相对于单层荧光 集光太阳能光伏器件,叠层荧光集光太阳能光伏器件能分波段充分利用太阳光谱,提高荧光集光太阳能光伏 器件的效率,进一步降低光伏发电的成本.但是,叠层荧光集光太阳能光伏器件涉及较多的参量,难以通过实验 优化.本文分析了从单层到叠层荧光集光太阳能光伏器件的全部物理过程,建立了数学模型,并相应编制了 计算机模拟软件.运用上述软件,系统研究了器件尺寸、太阳能电池的带隙对光电转换效率的影响.     

视场外激光干扰图像对目标获取性能的影响分析

以现有的目标获取性能模型NVLESD(Night Vision and Electronic Sensors Directorate)为基础,分析杂波对于"人在回路"目标获取性能的影响。针对视场外激光干扰图像的特点,运用图像边缘概率尺度修正后的目标获取性能模型对激光干扰图像进行分析。对CCD探测器的视场外干扰实验结果表明,该方法能够较好地反映激光干扰图像对于搜索探测概率的影响,从而验证了方法的有效性。     

大孔径双向聚能射孔弹的研究

 设计了一种双锥药型罩与双向装药结构相结合的聚能射孔弹模型,通过数值模拟方法研究其射流成型机理,并计算其射流参数。结果显示：双锥药型罩的小锥角部分形成聚能射流,大锥角部分形成翻转弹丸,射流头部和弹丸的速度分别为6 250 m/s和1 620.9 m/s,弹丸长度和平均直径分别为26.1 mm和8.6 mm。结合数值模拟结果,对射流侵彻公式进行了修正,并利用修正公式预测该射孔弹侵彻钢靶的深度,计算结果为69.6 mm。最后,按照该模型进行侵彻实验,实验回收弹丸的长度和平均直径分别为28.1 mm和8.8 mm,侵彻钢靶的深度和孔径分别为70 mm和17 mm。实验表明：数值模拟与理论计算方法相结合是可行的,能够有效地计算射孔弹的射流参数并预测其侵彻深度;该射孔弹侵彻性能优越。     

Thermodynamic Performance Characteristics of a Brownian Microscopic Heat Engine Driven by Discrete and Periodic Temperature Field

A Brownian microscopic heat engine with a particle hopping on a one-dimensional lattice driven by a discrete and periodic temperature field in a periodic sawtooth potential is investigated. In order to clarify the underlying physical pictures of the heat engine, the heat flow via the potential energy and the kinetic energy of the particles are considered simultaneously. Based on describing the jumps among the three states, the expressions of the efficiency and power output of the heat engine are derived analytically. The general performance characteristic curves are plotted by numerical calculation. It is found that the power output-efficiency curve is a loop-shaped one, which is similar to one for a real irreversible heat engine. The influence of the ratio of the temperature of the hot and cold reservoirs and the sawtooth potential on the maximum efficiency and power output is analyzed for some given parameters. When the heat flows via the kinetic energy is neglected, the power output-efficiency curve is an open-shaped one, which is similar to one for an endroeversible heat engine.     

不同部分进汽度及不同堵塞方式情况下的动叶片性能

本文对不同部分进汽度及不同堵塞方式情况下的调节级动叶片效率、流量和叶片升力等总体性能作了分析和总结,这些结果将对调节级动叶片的设计提供极为宝贵的参考。     

叶型偏差对整机环境中涡轮性能的影响

叶型加工和装配的误差可能会对涡轮部件乃至发动机整机的性能产生显著的影响。本文针对某整机环境中的涡轮部件,采用数值模拟结合实验的方法,研究了涡轮叶型偏差对其气动性能的影响。结果表明:在整机环境中,叶型偏差首先导致涡轮部件气动性能的微小变化,而整台发动机的工作点随之改变,导致涡轮部件的来流条件、各级涡轮的转速和速度三角形以及其内部的流动细节均会发生明显的变化,最终叶型偏差对涡轮部件气动性能的影响被显著放大。     

Misfit driven azimuthal orientation of NaCl domains on Ag(1 0 0)

We investigated the growth of thin NaCl films on Ag(1 0 0) by spot-profile-analysis low energy electron diffraction (SPA-LEED), varying extensively the growth temperature (200–500 K) and the film thickness (0.5–14 ML). The incommensurate growth of NaCl on Ag(1 0 0) yields (1 0 0)-terminated epitaxial NaCl domains, which are preferentially oriented with their [0 1 0] axis parallel to that of the substrate. At 300 K, the NaCl domains exhibit an azimuthal mosaicity by 14° around this orientation and the NaCl unit cell is laterally contracted in the first layers by 0.9% with respect to the bulk. At higher growth temperatures, the azimuthal mosaic distribution sharpens and additional distinct orientations appear, presumably due to a higher-order commensurability. The evolution of the azimuthal mosaic distribution with increasing temperature can be ascribed to both the NaCl thermal expansion and higher diffusion rates of NaCl on Ag(1 0 0). The best epitaxy, i.e. that with the highest selectivity of a specific azimuthal domain orientation, is achieved by growing NaCl films at low deposition rate (0.1 ML min⁻¹) on the Ag(1 0 0) substrate at constant high temperature (450–500 K). The observations made here can probably be applied more generally to other heterogeneous interfaces and, in particular, be used to improve the quality of thin insulating films.     

无沸腾喷雾冷却技术的研究进展

文中简述了无沸腾喷雾冷却技术近年来国内外的研究进展。着重介绍了关于影响无沸腾区换热各参数的实验研究,如壁面温度、介质体积通量、喷雾流量、喷雾倾角和喷雾高度等,为寻求最佳换热提供了指导。并对无沸腾区的理论研究内容进行了归纳,主要是模拟不同喷雾条件下的换热过程及特性参数(如液膜厚度)的大小和分布,并将理论值与实验数据进行比较分析;总结了影响无沸腾区换热的喷雾特性参数和外部特性。     

Scaling study of the combustion performance of gasben gas rocket injectors

To obtain the key subelements that may influence the scaling of gas-gas injector combustor performance, the combustion performance subelements in a liquid propellant rocket engine combustor are initially analysed based on the results of a previous study on the scaling of a gas-gas combustion flowfield. Analysis indicates that inner wall friction loss and heat-flux loss are two key issues in gaining the scaling criterion of the combustion performance. The similarity conditions of the inner wall friction loss and heat-flux loss in a gas-gas combustion chamber are obtained by theoretical analyses. Then the theoretical scaling criterion was obtained for the combustion performance, but it proved to be impractical. The criterion conditions, the wall friction and the heat flux are further analysed in detail to obtain the specific engineering scaling criterion of the combustion performance. The results indicate that when the inner flowfields in the combustors are similar, the combustor wall shear stress will have similar distributions qualitatively and will be directly proportional to p_c^0.8 d_t^-0.2 quantitatively. In addition, the combustion peformance will remain unchanged. Furthermore, multi-element injector chambers with different geometric sizes and at different pressures are numerically simulated and the wall shear stress and combustion efficiencies are solved and compared with each other. A multi-element injector chamber is designed and hot-fire tested at several chamber pressures and the combustion performances are measured in a total of nine hot-fire tests. The numerical and experimental results verified the similarities among combustor wall shear stress and combustion performances at different chamber pressures and geometries, with the criterion applied.