Radiative and hybrid cooling of infrared space telescopes

The designs of cold space telescopes, cryogenic and radiatively cooled, are similar in most elements and both benefit from orbits distant from the Earth. In particular such orbits allow the anti-sunward side of radiatively-cooled spacecraft to be used to provide large cooling radiators for the individual radiation shields. Designs incorporating these features have predictedT _tel near 20 K. The attainability of such temperatures is supported by limited practical experience (IRAS, COBE). Supplementary cooling systems (cryogens, mechanical coolers) can be advantageously combined with radiative cooling in hybrid designs to provide robustness against deterioration and yet lower temperatures for detectors, instruments, and even the whole telescope. The possibility of such major additional gains is illustrated by the Very Cold Telescope option under study forEdison, which should offerT _tel5 K for a little extra mechanical cooling capacity.     

积垢对离心压气机性能的影响分析

以某型离心压气机为研究对象,利用流场仿真软件对不同污染程度的压气机性能进行数值计算,对比流场特性的变化,分析了积垢造成压气机性能损失的程度。结果表明：积垢对离心压气机性能的主要影响是降低压气机效率,原因是积垢改变了叶片表面粗糙度,增加了摩擦损失;扩大了叶片后缘和出口附近的低速回流区的范围,增强了回流强度,加大了流动损失。     

The Edison infrared space observatory

For five years, theEdison program has had the goal of developing new designs for infrared space observatories which will break the cost curve by permitting more capable missions at lower cost. Most notably, this has produced a series of models for purely radiative and radiative/mechanical (hybrid) cooling which do not use cryogens and optical designs which are not constrained by the coolant tanks. Purely radiatively-cooled models achieve equilibrium temperatures as low as about 20 K at a distance of 1 AU from the sun. More advancedEdison designs include mechanical cooling systems attached to the telescope assembly which lower the optical system temperature to 5 K or less. Via these designs, near-cryogenic temperatures appear achievable without the limitations of cryogenic cooling. OneEdison model has been proposed to the European Space Agency as the next generation infrared space observatory and is presently under consideration as a candidate ESA Cornerstone mission. The basic design is also the starting point for elements of future infrared space interferometers.     

Optimised radiative cooling of infrared space telescopes and applications to possible missions

General principles are outlined for the design of space infrared telescopes intended to cool by radiation to the lowest temperatures attainable without the use of on-board cryogens, and assuming on-orbit cooling after a warm launch. Maximum protection from solar and earth heating, maximum radiating area and efficiency and minimum absorbing area and absorptivity are the obvious basic criteria. The optimised design is a short, fat telescope surrounded by a series of radiation shields, each cooled by its own radiator. Maximising the longitudinal conductivity of the radiation shields and of the telescope tube itself is important both to the on-orbit cooling time and the final achieveable temperature. Realistic designs take between 80 and 200 days to cool to within a few degrees of equilibrium temperatures, depending on the materials used. Great advantages accrue from the use of an orbit distant from earth. Both simple models and detailed simulations suggest that temperatures of 30 to 40 K are attainable in high earth orbits. Placing a radiatively cooled telescope in a halo orbit around the Lagrangian point L2 is a particularly attractive option and significantly lower temperatures can be achieved there than in Earth orbit. Optimised radiative cooling is an important element of the small Japanese mission SMIRT. We suggest that a combination of an ESA Medium-sized Mission with a NASA Explorer to send a 2m+ telescope to an L2 halo orbit would provide a cost-effective and powerful long-duration facility for the early 21st century.     

逆波兰式优化算法在航空发动机测试系统中的应用

为了适应新一代航空发动机测试系统的发展要求,提高测试系统对计算参数的处理能力,结合航空发动机测试系统的自身特点,将逆波兰式算法应用到测试系统的参数计算中,并对逆波兰式算法进行改进和优化。结果表明:逆波兰式算法可提高发动机测试系统代码的可移植性与重复性,优化后的逆波兰式算法可提高测试系统的容错性、计算结果准确性,从计算程序的运行时间来看,优化后的算法较未优化算法的计算效率提高20%~40%。     

Human space exploration and human spaceflight: Latency and the cognitive scale of the universe

The role of telerobotics for space exploration in placing human cognition on other worlds is limited almost entirely by the speed of light, and the consequent communications latency that results from large distances. This latency is the time delay between the human brain at one end, and the telerobotic effector and sensor at the other end. While telerobotics and virtual presence is a technology that is rapidly becoming more sophisticated, with strong commercial interest on the Earth, this time delay, along with the neurological timescale of a human being, quantitatively defines the cognitive horizon for any locale in space. That is, how distant can an operator be from a robot and not be significantly impacted by latency? We explore that cognitive timescale of the universe, and consider the implications for telerobotics, human spaceflight, and participation by larger numbers of people in space exploration. We conclude that, with advanced telepresence, sophisticated robots could be operated with high cognition throughout a lunar hemisphere by astronauts within a station at an Earth-Moon L1 or L2 venue. Likewise, complex telerobotic servicing of satellites in geosynchronous orbit can be carried out from suitable terrestrial stations.     

面向空间应用的大容量实时网络总线架构

针对未来空间综合电子系统总线网络发展需求,本文在介绍现有星载电子系统体系架构优缺点的基础上,提出了一种面向空间环境应用的高速高可靠实时网络总线架构。对网络协议架构、网络拓扑、工作原理及网络关键设备进行了详细介绍,该技术10 Gb/s的传输带宽、亚微秒时钟同步精度、多通道冗余传输机制能够满足未来空间环境应用需求,为未来空间电子系统网络架构研究提供借鉴。     

聚乙撑二氧噻吩/碳纳米管复合物的合成与表征

为制备出导电性能优良的有机透明导电涂层,需要把具有导电性的碳纳米管在树脂中组装成一体化导电结构网络.本文运用可以在树脂中自组装的导电聚乙撑二氧噻吩来实现碳纳米管自组装的方法,合成出了导电聚乙撑二氧噻吩纳米薄膜均匀覆盖的导电聚乙撑二氧噻吩/碳纳米管复合物,并运用透射电镜(TEM)、傅立叶红外光谱(FTIR)和四探针法对其进行了分析与表征,结果发现在碳纳米管含量为1%时,纳米复合物的导电率可达到100S/cm,而碳纳米管和聚乙撑二氧噻吩的导电率分别为10.4 S/cm和14.3S/cm.     

氟橡胶-金属胶粘剂的研究

针对氟橡胶与金属的粘接难题,制备改性Chemlok 607,OG,OG’和OGs四种胶粘剂,与国内合神FA-1、国外Chemlok 607胶粘剂进行对比研究。结果表明,这四种胶粘剂用于未硫化氟橡胶与金属粘接时拉剪强度均远大于FA-1和Chemlok 607。改性Chemlok 607胶粘剂较好地解决了硅烷类胶粘剂与金属粘接性不好的问题。OG,OG’和OGs胶粘剂均可直接用于未硫化氟橡胶与金属的粘接,也可用于硅橡胶的粘接,是氟橡胶与金属粘接用的优良胶粘剂,目前已试用于汽车同步环中氟橡胶与金属的粘接。通过热失重分析(TGA)研究表明,OG,OG’和OGs胶粘剂固化物具有较高的耐热性及热稳定性。二氨基二苯砜(DDS)固化时会与氟橡胶在粘接界面处生成配位键,改善与氟橡胶的粘接性能,提高粘接强度。     

基于高斯混合模型的发动机稳态数据特征值提取方法

因航空发动机的工作环境及工作特性所致,其稳态试验数据常伴有噪声干扰,对稳态值计算结果的准确性造成影响。在对稳态数据进行正态性检验后,利用稳态数据来源的正态特性,以及利用混合模型对数据的良好回归特性,基于高斯混合模型对稳态数据进行筛选分类。依托发动机稳态数据分布形式的相近性与数据本身的统计特性,来确定稳态数据特征值的提取方法。在对发动机稳态数据进行数据筛选以及对比不同稳态数据片段后,验证模型方法的数据降噪效果以及稳态数据特征值计算结果与同一稳定工作状态数据片段的选取不相关性。结果表明：从仿真数据的筛选结果以及不同稳态数据片段的验证结果可知,该方法具有较强的稳定性,可有效筛选出发动机稳态点数据,并准确计算出发动机稳态值,一般收敛结果相对误差在0.2%以内。