空间核电源热管式辐射散热器热分析与参数优化

针对空间热管辐射散热器的特殊工况对散热器进行热分析建模，通过分析其传热原理，建立出热阻模型，并通过和实际设计进行对比，验证模型和计算方法的可行性。选取翅根温度、翅片长度和翅片厚度等参量作为约束条件，分别对热管式空间辐射散热器的翅片散热效率和系统质量特性进行优化分析，获得最优设计参数。     

新型行波光调制器单脊波导的微波电路研究

设计了一种采用单脊波导作为微波电路的新型行波光调制器。分析计算了脊缝间距小于１．００ｍｍ的脊波导中的电场分布、截止波长、频带宽度和特性阻抗；设计了与矩形波导联接的过渡段。结果表明：采用单脊波导作为光调器将使微波电场得到充分的利用，将提高调制效率；使波导单模工作频带增宽；具有较低的特性阻抗；通过过渡段易与矩形波导联接及保证单模传输。最后，经论证选择了切实可行的脊波导各几何参数ａ＝１３．００ｍｍ，ｂ＝１０．１６ｍｍ，ｄ＝０．５０ｍｍ，ｓ＝１．００ｍｍ。     

Global GPS reference frame solutions of unlimited size

This paper reports on the Dancer project, which is one of three related projects initiated by working group 1 of the International Association of Geodesy. The Dancer project develops JAVA parameter estimation software that runs in the form of a distributed process on the internet, in such a way that each processing node handles the data of a single geodetic instrument. By exchanging a minimum amount of information among all processing nodes, the same global normal equation solution is found by all instruments. The result is a fully scalable least squares solution that has no practical limit to the number of GPS receivers or other tracking devices that may be included in a single reference frame realization.     

Constant power H∞ stabilization control strategy on airborne pump supplying system

以机载泵源系统的恒功率控制为目标，针对作业任务中系统负载随时间变化的情况，采用使液压系统输出功率保持恒定的控制方式来达到充分利用发动机功率的目的，对于机载泵源控制系统的主要被控对象——轴向柱塞式变量泵，建立了其状态方程和流量输出方程，采用H。鲁棒镇定控制策略实时调节泵的排量，仿真结果表明：当负载变化时，系统能根据压力的变化快速转换到恒功率工作曲线下对应的流量状态，所设计的H。控制器能够减小干扰和模型参数不确定对系统稳定性的影响，具有良好的鲁棒性，表明该方法用于机载液压系统可以改善系统工作性能，提高系统功率的利用率。     

Development of Kabila rocket: A radioisotope heated thermionic plasma rocket engine

A new type of plasma rocket engine, the Kabila rocket, using a radioisotope heated thermionic heating chamber instead of a conventional combustion chamber or catalyst bed is introduced and it achieves specific impulses similar to the ones of conventional solid and bipropellant rockets. Curium-244 is chosen as a radioisotope heat source and a thermal reductive layer is also used to obtain precise thermionic emissions. The self-sufficiency principle is applied by simultaneously heating up the emitting material with the radioisotope decay heat and by powering the different valves of the plasma rocket engine with the same radioisotope decay heat using a radioisotope thermoelectric generator. This rocket engine is then benchmarked against a 1 N hydrazine thruster configuration operated on one of the Pleiades-HR-1 constellation spacecraft. A maximal specific impulse and power saving of respectively 529 s and 32% are achieved with helium as propellant.Its advantages are its power saving capability, high specific impulses and simultaneous ease of storage and restart. It can however be extremely voluminous and potentially hazardous. The Kabila rocket is found to bring great benefits to the existing spacecraft and further research should optimize its geometric characteristics and investigate the physical principals of its operation.     

高精度光栅干涉测量技术及仪器

在超精密测量和控制技术中，对测量精度提出了越来越高的要求，如尺寸精度１ｎｍ和角度０．００１。由于光栅具有精度高、抗干扰能力强、寿命长和价格便宜等优点，最近几年光栅干涉测量技术被广泛研究和使用。本文简单介绍几种在超精密测量和制造过程中常用的微纳米光栅干涉测量技术。     

Working processes in the solid-propellant low-temperature aerosol generator with an inert heatexchanger

Alignment charts that make it possible to select a standard size of inert heatexchanger structures with specified output characteristics and a developed scheme of the low-temperature aerosol generator are presented.     

保证数字系统可靠性的容错设计

通过比较元件级余裕模式和系统级余裕模式的设计优势，探讨了提高数字系统可靠性的元件级余裕模式和系统级余裕模式的设计方法，为保证数字系统的可靠性提供了设计根据。     

双温双压法湿度测量不确定度的综合评定

基于双温双压法的湿度发生过程受到温度、握力、饱和度、增强因子等多种因素的影响，如何解决各参数之间的耦合问题，并将所有因素引入湿度测量不确定度评定模型是提高湿度测量准确度的重要方法。详细分析了增强凶子和饱和器的饱和度对实验舱湿度的影响，提出一种完整的评定模型及解算方法，并通过实例说明该模型的应用及其对评定结果的影响。