Performance of a simple Closed Aquatic Ecosystem (CAES) in space.

A simple Closed Aquatic Ecosystem (CAES) consisting of single-celled green algae (Chlorella pyrenoidosa, producer), a spiral snail (Bulinus australianus, consumer) and a data acquisition and control unit was flown on the Chinese Spacecraft SHENZHOU-II in January 2001 for 7 days. In order to study the effect of microgravity on the operation of CAES, a 1 g centrifuge reference group in space, a ground 1 g reference group and a ground 1 g centrifuge reference group (1.4 g group) were run concurrently. Real-time data about algae biomass (calculated from transmission light intensity), temperature, light and centrifugation of the CAES were logged at minute intervals. It was found that algae biomass of both the microgravity group and the ground 1 g-centrifuge reference group (1.4 g) fluctuated during the experiment, but the algae biomass of the 1 g centrifuge reference group in space and the ground 1 g reference group increased during the experiment. The results may be attributable to influences of microgravity and 1.4 g gravity on the algae and snails metabolisms. Microgravity is the main factor to affect the operation of CAES in space and the contribution of microgravity to the effect was also estimated. These data may be valuable for the establishment of a complex CELSS in the future.     

双CPU环境下飞行控制软件的设计

本文介绍运载火箭飞行控制软件在双ＣＰＵ冗余硬件配置下的可靠性设计和可靠性指标分配的方法。文中提到的部分技术经过了实验的检验，证明是可行的     

长盛不衰 百年犹荣--一个颇具盛名的标准化团体ASTM

回顾了ＡＳＴＭ的建立过程，该机构目前已有３００００多个国内外会员，１３１个技术委员会，每年都出版标准年鉴，标准被世界各国广泛采用，与美国国防部标准化部门及其他标准化机构有广泛的联系，活动经费主要依靠出售标准和提供标准化服务的收入。     

基于ADS仿真的锁相环设计与实现

文章利用MAX2620构造宽带可调VCO并用ADS建模进行参数优化，在此基础上与MB15E03频率合成芯片构造锁相环，并利用ADS对暂态响应和相位噪声性能进行分析，在仿真分析的基础上建立实际的锁相环电路。     

“Ⅳ型”激波干扰中流-热-固耦合问题一体化计算分析

针对高超声速进气道前缘"Ⅳ型"激波干扰产生的气动加热与结构传热多物理场耦合计算问题，发展了一种基于有限体积法的流-热-固一体化计算方法。该方法采用一体化控制方程组统一离散求解外部高速流场与内部结构温度场，规避了传统分区耦合算法在时间域内交替迭代的繁琐数据交换策略。另外，提出一种新的双温阻模型计算流-固交界面的物性参数以保证计算准确性，采用LU-SGS隐式时间迭代和自适应时间步长以提高计算效率。采用经典高超声速二维圆管流-热-固耦合算例对该一体化方法进行验证，计算结果与试验值和参考文献数据吻合较好，证明了该方法的可靠性和正确性。利用一体化方法对高超声速前缘"Ⅳ型"激波干扰流-热-固耦合问题进行定常/非定常计算与分析，给出了温度与热流的时变特性，计算结果表明，激波干扰作用产生的超声速"喷流"不断冲击壁面，使得壁面最大压力系数增大约9倍，壁面最大热流增大约4.7倍，给高速飞行器的热防护设计与选材带来严峻挑战。同时，也表明了一体化计算方法可以较好地用于长航时飞行条件下与复杂飞行环境下的高超声速热防护系统的热环境特性分析与综合性能评估。     

A tentative statistical analysis of flare events observed by NoRH and NoRP

In this paper, we report the statistical analysis of flare events observed by NoRH during 1992–2005 and NoRP during 1994–2005. We give the power law indices for the frequency distribution of peak brightness temperature which is 1.87 ± 0.05 for 17 GHz observation and is 1.64 ± 0.04 for 34 GHz observation. We also present the frequency variation of power law indices for peak flux and total energy of flare for NoRP observation, which is mono-increasing from 1 to 17 GHz.     

多电飞机大功率高压直流起动发电机系统研究与实现

起动发电（SG）一体化是多电飞机（MEA）和全电飞机（AEA）机载主电源系统的重要特征与关键技术。高压直流电源（HVDC）系统输出不受交流电频率约束，电机可工作在更高转速从而提高功率密度，且易于并联提高供电可靠性，已经成为飞机电源系统的重要发展方向。提出三级式高压直流起动发电系统架构，阐述了其组成和工作原理，分析了发电和起动模态下永磁发电机（PMG）、励磁机（ME）和主电机（MG）的运行特性，以及发电模态下励磁机的恒流源和电流放大器特性；研究了起动模态下主电机的转矩产生机理和影响因素以及励磁机单相交流励磁特性。研制成功120 kW/270 V高压直流起动发电机系统，构建起动发电一体化实验平台，完成了发电及发动机模拟起动运行实验，实验与仿真结果一致，为大功率高压直流起动发电系统在新一代飞机上的应用奠定了理论和技术基础。     

发动机缸体水套热芯盒模具在生产中存在的问题及解决方案

以发动机缸体水套为例着重论述了热芯盒模具在使用中存在的问题,并针对这些问题提出了解决方案,为以后的设计积累经验。     

Two freedom linear parameter varying μ synthesis control for flight environment testbed

To solve the problem of robust servo performance of Flight Environment Testbed(FET)of Altitude Ground Test Facilities(AGTF) over the whole operational envelope, a two-degree-offreedom μ synthesis method based on Linear Parameter Varying(LPV) schematic is proposed, and meanwhile a new structure frame of μ synthesis control on two degrees of freedom with double integral and weighting functions is presented, which constitutes a core support part of the paper. Aimed at the problem of reference command's rapid change, one freedom feed forward is adopted, while another freedom output feedback is used to meet good servo tracking as well as disturbance and noise rejection; furthermore, to overcome the overshoot problem and acquire dynamic tuning,the integral is introduced in inner loop, and another integral controller is used in outer loop in order to guarantee steady errors; additionally, two performance weighting functions are designed to achieve robust specialty and control energy limit considering the uncertainties in system. As the schedule parameters change over large flight envelope, the stability of closed-loop LPV system is proved using Lyapunov inequalities. The simulation results show that the relative tracking errors of temperature and pressure are less than 0.5% with LPV μ synthesis controller. Meanwhile, compared with non-LPV μ synthesis controller in large uncertainty range, the proposed approach in this research can ensure robust servo performance of FET over the whole operational envelope.     

PLC双行车全自动控制程序的设计

本文介绍了使用ＰＬＣ对两台车进行全自动控制的程序设计过程，重点 利用表格法驱动行车的方案和具体实现方法。