Design of a canard configured TransCruiser using CEASIOM

CEASIOM is a multidisciplinary software environment for aircraft design that has been developed as part of the European Framework 6 SimSAC project. It closely integrates discipline-specific tools such as those used for CAD, grid generation, CFD, stability analysis and control system design. The environment allows the user to take an initial design from geometry definition and aerodynamics generation through to full six degrees of freedom simulation and analysis. Key capabilities include variable fidelity aerodynamics tools and aeroelasticity modules. The purpose of this paper is to demonstrate the potential of CEASIOM by presenting the results of a Design, Simulate and Evaluate (DSE) exercise applied to a novel, project specific, transonic cruiser configuration called the TCR. The baseline TCR configuration is first defined using conventional methods, which is then refined and improved within the CEASIOM software environment. A wind tunnel model of this final configuration was then constructed, tested and used to verify the results generated using CEASIOM.     

高效相变蓄热装置结构设计及试验研究

文章针对某飞行器舱内大功率设备控温需求,提出了相变蓄热技术解决方案,建立了平板式肋片强化相变蓄热装置物理模型,根据大功率伺服舵机控制器热耗及工作模式等参数条件,采用十八烷为相变吸热材料,设计了一台高效平板式肋片相变蓄热装置,并通过地面试验研究,验证了该装置的控温性能、稳定性及等温性。试验结果表明:所设计的肋片式高效相变蓄热装置,在120 W热源功率下,可以将设备温度控制在50℃以下超过3000 s;榫槽形式的封装结构具有良好的密封性能,相变蓄热装置在多次相变循环后无泄漏;在3000 s测试时间内相变装置内部最大温差为3℃,具有很好的等温性。     

10 Differences between Shenzhou 8 and Shenzhou 9 Missions

Generally, the Shenzhou 8 and Shenzhou 9 spaceships were similar in technology status. As the Shenzhou 9 spaceship implemented the manned rendezvous and docking mission, the program was appropriately modified. There are 10 primary differences between the two missions.     

基于代理模型的大型民机机翼气动优化设计

先进的气动优化设计思想与方法，对于提升大型民机气动与综合性能具有至关重要的意义。探讨了大型民机超临界机翼气动优化设计的基本准则和要点，并结合代理优化算法，提出了一种面向工程应用的多轮次高效全局气动优化设计方法。首先，通过一系列解析函数/翼型/机翼优化测试算例进行了验证。其次，将所提出的方法与人工修型相结合，开展了针对宽体客机超临界机翼的两轮气动优化设计，使其气动性能得到显著改善。最后，采用不同的雷诺平均Navier-Stokes（RANS）方程求解器对安装优化机翼的全机巡航构型进行了典型状态的气动性能综合评估。研究结果表明，所提出的代理优化算法具有很高的优化效率、较强的约束处理和全局优化能力；将所发展的基于代理模型的多轮次气动优化设计方法与人工修型相结合，能够获得满足设计要求的气动外形，验证了该方法在大型民机超临界机翼气动设计中的有效性和工程实用性。     

面向对象技术的防空导弹Simulink建模与仿真

为防空导弹系统性能改进研究和优化设计,提出了一种新的方法,首先给出了一般防空导弹制导控制系统的数学模型,并采用面向对象建模技术结合动态仿真软件Simulink建立了仿真模型并进行了仿真研究,该模型具有容易理解,可重复使用,易于扩展等优点,即通过部分模块更换或改变参数等就可对该系统在其他条件下进行仿真,仿真结果和实际遥测数据基本吻合,表明了该模型和方法的有效性和实用性。     

双混频时差测量系统设计中的理论和技术问题

从分析双混频时差(DMTD)测量系统的测量误差着手,对系统设计和使用中常磁到的一些理论和技术问题进行了探讨,这涉及到公共源的影响、移相器的作用、自校和测量中的其它问题。     

The relation between the Black hole mass and the Bulge mass for low redshift AGNs. Part I: Ground-based observations

Using the bulge data from AGN image decomposition with ground-based observations, we calculate the ratios of the central supermassive black hole mass(SMBH) to the Bulge mass (_Mbh/_Mbulge$M_{\text{bh}}/M_{\text{bulge}}$) in a sample of X-ray selected AGNs, including 15 Narrow-line Seyfert 1 galaxies (NLS1s) and 18 broad-line Seyfert 1 galaxies (BLS1s). We found that the mean value of log(_Mbh/_Mbulge)$\log (M_{\text{bh}}/M_{\text{bulge}})$ is -3.81±0.11$-3.81\pm 0.11$ for 15 NLS1s, and -2.91±0.13$-2.91\pm 0.13$ for 18 BLS1s, showing the lower _Mbh/_Mbulge$M_{\text{bh}}/M_{\text{bulge}}$ in NLS1s relative to BLS1s. The calculation shows that the Bulge mass from the host image decomposition in NLS1s is statistically smaller than that from Hubble-type correction method, and a linear mass relation is suggested for NLS1s and a nonlinear mass relation for BLS1s. The studying of host galaxies with ground-based observations strongly limited by the atmospheric seeing. We need to do the decomposition of host images for NLS1s with Hubble Space Telescope observation in the future.     

基于CPLD的高速可重构PCM帧同步器的实现

给出一种基于 CPL D的高速可重构帧同步器的设计思路和实现方法 ,探讨如何提高系统速度及其可靠性。既采用数字化相关检测技术和可容错的校验保护技术 ,又采用系统内在线可编程 ISP(In- System Programm ing)技术和提高系统速度的流水线技术 ,综合高速 PCI总线接口设计 ,完成了在线可重新配置的高速帧同步器的实现     

柔性夹具设计方法与技术

针对ＦＭＳ中夹具设计、制造、组装准备系统自动化程度低的现状,重点分析了柔性夹具设计依据、特点、设计方法,可为其它ＦＭＳ柔性夹具的设计提供参考依据。