再入飞行器表面磁流体发电装置数值模拟

提出了钝锥型再入飞行器上的表面磁流体发电装置方案,采用低磁雷诺数近似下的磁流体力学模型对其进行了流动与静电场耦合的数值模拟,由此建立了表面磁流体发电装置中的物理图像.数值模拟结果表明,在典型再入条件(飞行高度46 km,速度7 km/s)下,所提出表面磁流体发电装置方案能够实现兆瓦级(电功率1.28MW)能量输出,电能提取导致再入飞行器阻力增大13.7%,对飞行器壁面总热流值的影响并不显著,但发电区域及其下游壁面的热流密度分布发生明显变化,该区域内热流密度峰值发生于电极的前、后缘.     

CREAM: 70 days of flight from 2 launches in Antarctica

The Cosmic-Ray Energetics And Mass balloon-borne experiment has been launched twice in Antarctica, first in December 2004 and again in December 2005. It circumnavigated the South Pole three times during the first flight, which set a flight duration record of 42 days. A cumulative duration of 70 days within 13 months was achieved when the second flight completed 28 days during two circumnavigations of the Pole on 13 January 2006. Both the science instrument and support systems functioned extremely well, and a total 117 GB of data including 67 million science events were collected during these two flights. Preliminary analysis indicates that the data extend well above 100 TeV and follow reasonable power laws. The payload recovered from the first flight has been refurbished for the third flight in 2007, whereas the payload from the second flight is being refurbished to be ready for the fourth flight in 2008. Each flight will extend the reach of precise cosmic-ray composition measurements to energies not previously possible.     

发动机燃气喷流红外辐射场的数值模拟

在高温流动中热辐射与流场是耦合的,但在发动机燃气喷流流场的温度范围内可以在流场计算中忽略热辐射的影响,于是流场与辐射场的模型方程可解耦.为此提出了模拟飞行器绕流流场红外辐射的解耦模型以及相应的算法.该算法首先采用总变差减小TVD(Total Variation Diminishing)格式对流场进行模拟,再引入有限体积概念,应用所取得的流场参数,在同一组网格上计算流场中的红外辐射特征.以轴对称喷管内N₂,O₂,CO₂,H₂O,CO,HCl,H₂等7组分高度欠膨胀冻结流与均匀绕流干扰流场为算例进行了验证性的模拟计算,并与已有试验和计算数据进行了对比,表明该算法是可靠的,可在较大幅度地降低计算量的情况下给出满足工程需要的结果.     

快速大时间步长熵条件格式的分辨率研究

提出了高分辨率快速大时间步长熵条件格式的构造方法.用激波管问题对一族熵条件格式进行研究.在精度、步长、限制器方面进行了详细的数值实验,研究了同样计算量下各种格式的表现品质.从理论上保证了大时间步长格式的无振荡性质,从具体的数值实验分析中确定了大时间步长格式的分辨率问题.      

高超声速飞行器尾喷管的优化设计

以喷管上壁折转角、下壁长度、舵面长度及其折转角为设计变量,结合遗传算法和特征线法对高超声速飞行器尾喷管进行了优化设计,并对设计变量进行了参数研究.结果表明,所采用的优化设计方法计算效率高且比较准确,特别适合于高超声速飞行器尾喷管的优化设计;所采用的4个设计参数均能有效地影响尾喷管的气动性能,其中喷管上壁折转角和舵面折转角分别对喷管的升力和推力的影响相对明显,对其进行均衡选择方能得到最优的结果.      

CME Theory and Models

This chapter provides an overview of current efforts in the theory and modeling of CMEs. Five key areas are discussed: (1) CME initiation; (2) CME evolution and propagation; (3) the structure of interplanetary CMEs derived from flux rope modeling; (4) CME shock formation in the inner corona; and (5) particle acceleration and transport at CME driven shocks. In the section on CME initiation three contemporary models are highlighted. Two of these focus on how energy stored in the coronal magnetic field can be released violently to drive CMEs. The third model assumes that CMEs can be directly driven by currents from below the photosphere. CMEs evolve considerably as they expand from the magnetically dominated lower corona into the advectively dominated solar wind. The section on evolution and propagation presents two approaches to the problem. One is primarily analytical and focuses on the key physical processes involved. The other is primarily numerical and illustrates the complexity of possible interactions between the CME and the ambient medium. The section on flux rope fitting reviews the accuracy and reliability of various methods. The section on shock formation considers the effect of the rapid decrease in the magnetic field and plasma density with height. Finally, in the section on particle acceleration and transport, some recent developments in the theory of diffusive particle acceleration at CME shocks are discussed. These include efforts to combine self-consistently the process of particle acceleration in the vicinity of the shock with the subsequent escape and transport of particles to distant regions.     

CIR Morphology, Turbulence, Discontinuities, and Energetic Particles

Corotating interaction regions (CIRs) in the middle heliosphere have distinct morphological features and associated patterns of turbulence and energetic particles. This report summarizes current understanding of those features and patterns, discusses how they can vary from case to case and with distance from the Sun and possible causes of those variations, presents an analytical model of the morphological features found in earlier qualitative models and numerical simulations, and identifies aspects of the features and patterns that have yet to be resolved. This revised version was published online in August 2006 with corrections to the Cover Date.     

发动机维护服务的现状与未来

航空发动机大修业务开始企稳,而且预计未来还将有所增加. 据MRO Prospector统计,目前在役的窄体飞机机队数量约是宽体飞机的3倍,2011年窄体飞机的发动机返厂维修量将会有大幅增加.     

Algorithms for Power Converter Design Optimization

A practical optimization approach for power converters is established which allows conception of a design to meet all powercircuit performance requirements and concurrently to optimize a defined quantity such as weight or losses. In addition to facilitating a cost effective design, the computer-aided approach provides a means to readily assess a) the weight-efficiency tradeoff, b) impacts of converter requirements and component characteristics on a given design, and c) optimum power-system configurations. The following two popular algorithms for nonlinearly constrained optimization are utilized to design the power converter: 1) the sequential unconstrained minimization technique, SUMT Version 4; 2) the ALAG penalty function technique, ALAG5. These algorithms are compared, and suggestions are made for improving the efficiency of the optimization algorithms for power converter design.     

An LS-TLS-based sequential identification algorithm: Application toan accelerometer

Total least squares (TLS) parameter estimation is an alternative to least squares (LS) estimation when there are errors in both data matrix and observation vector. Especially, when some of the columns, not all, of the data matrix A are free of error, we call it a mixed LS-TLS problem. Accordingly, a sequential algorithm for solving a mixed LS-TLS problem is proposed here. The proposed algorithm employs an efficient algorithm to locate the minimum eigenpair, instead of singular value decomposition (SVD) which is computationally exacting. The proposed algorithm is applied to an accelerometer model to identify error parameters which are very important in inertial navigation systems (INS)