Space technology transfer: Spin-off cases from Japan

Government organizations have to justify high expenditure during periods of financial crisis such as the one we are experiencing today. Space agencies have attempted to increase the returns on their investments in space missions by encouraging the commercial use of advanced technologies. This paper describes two technology transfer (TT) cases promoted by JAXA, in order to identify the organizational models and determinants of TT. The development of a TT process from space to Earth not only benefits the aerospace industry but also the network of national companies. The aim of the paper is to investigate who the actors are and the nature of their role, as well as the determinants of the TT process in the Japanese space sector. The case studies confirm the typical path of transfer as ‘Earth–space–Earth’.     

低温推进剂输送与预冷系统间歇泉不稳定性数值模拟研究

针对低温推进剂（液氧）输送与预冷系统间歇泉不稳定性进行了模拟与数值试验研究。分析与验证了连接液氧贮箱的底端封闭垂直管路的典型间歇泉不稳定过程,对经验Murphy曲线进行了检验。针对自然循环型的低温推进剂输送与预冷系统不稳定性及典型间歇泉的发生,进行了稳定域的计算与影响参数分析,研究了过冷度、输送管漏热、发动机进出口阻力、回路高度,以及回流管漏热（保温状况）对各域边界的影响。     

空间非合作目标消旋技术研究现状总结与展望

针对空间非合作目标开展在轨服务、轨道清除等需要在轨捕获任务的顺利实施,在捕获前一般需要对非合作目标进行消旋。系统调研了国内外针对空间非合作目标的消旋方案,并将其分为基于能量转移和基于能量损耗的两种方案。在对两类方案的具体原理及操作过程与关键技术进行总结的基础上,概括了各方案的特性及其适用场景,分析了未来空间非合作目标消旋技术的发展方向。     

一种深空天文测角导航中的星历误差抑制方法

以火星探测器为例，提出一种以星光角距/时间差分星光角距作为量测量的星历误差抑制方法，分析了火卫一星历误差对导航精度的影响，建立了火卫一时间差分星光角距的量测模型。通过将火星星光角距和火卫一星光角距相结合，发挥了两种量测的优势，实现了对火卫一星历误差的抑制。仿真结果表明，基于星光角距/时间差分星光角距天文导航方法的位置误差是传统基于星光角距天文导航方法的64%，是基于时间差分星光角距导航方法的58%。此外，还分析了导航恒星个数、火星敏感器精度、火卫一敏感器精度、星历误差大小和滤波周期对导航性能的影响。     

氧化物玻璃中 Eu￣(3+) 离子的敏化发光与能量传递

研究了氧化物玻璃中Ｅｕ３＋离子的敏化发光。结果表明，硅酸盐玻璃中Ｂｉ３＋向Ｅｕ３＋离子产生共振能量转移而对Ｅｕ３＋发光起敏化作用；磷酸盐玻璃中，Ｐｒ３＋，Ｓｍ３＋对Ｅｕ３＋离子产生特征激发敏化发光，提出了声子支助的共振能量转移模型，解释了Ｅｕ３＋的敏化发光。     

动态系统时延参数估计的重构输入法

首先指出了过去在进行时延系统参数估计时所用的近似处理方法的弊端，然后就动态系统未知时延参数的估计问题提出了重构系统输入的估计方法，并以极大似然估计迭代算法为基础给出了一套估计动态系统时延参数的算法，最后，应用所提出的方法进行了仿真计算，仿真结果表明，参数估计的精度极高，这说明该方法是可靠且可行的。     

Establishing space industry in developing countries: Opportunities and difficulties

Although it is generally agreed that the outer space should be used for the benefit of all mankind, only a fraction of the countries have the necessary technological base for accessing space. Space technology, with its implications on science, economy and well-being of citizens, is mostly chosen as one of the priority areas for technological development by developing countries. However, there is already an over-capacity in global space industry and there are doubts on necessity of additional capacity establishment by developing countries. In this study, the importance and benefits of capacity-building in these countries are emphasized and the advantages and disadvantages that developing countries have in the framework of space technology acquisition are briefly presented. The feasibility of certain levels of space technology is discussed and the necessity of combining existing indigenous capabilities with technology obtained from foreign sources in the optimal way is stressed. We have also mentioned various general mechanisms of technology transfer and argued the importance of licensing in catching-up developed countries. After considering the necessary conditions of efficiency of technology, such as establishment of regional centers of space science and technology education by United Nations, joint development of space systems, complete technology transfer packages, cooperative space projects within regional organizations, coordinated constellations and special agreements with large space agencies, which are specific mechanisms already in use, are reviewed. Some typical examples of mechanisms are also given with special emphasize on small satellite technology that makes access to space affordable for many countries. Through sharing and analyzing the experience of developing countries in their odyssey of space capacity-building, the difficulties can be negotiated and the vicious circles can be broken. This study, in our view, is a step to incite a general discussion of obstacles and opportunities for developing countries, that could help them in using their limited resources effectively, hence, enable them to offer better conditions to their citizens and to contribute space science to a larger extend.     

变厚度圆锥壳的传递函数解

采用多参量渐近分布参数传递函数法，分析了变圆锥壳的静变形和自由振动问题。文中利用Fourier级数展开，Laplace变换，推导了变厚度圆锥壳状态空间形式的运动微分方程。在圆锥壳渐近传递函数解的基础上，再引入一个与厚度变化相关的小参数。利用摄动方法，将微分方程进行双参层摄动，采用传递函汉对所得到的摄动方程进行求解，得到了变厚度圆锥壳在任意边界条件下的渐近传递函数解。     

A rendezvous navigation algorithm for orbit determination, based on visual measurements by space vehicle crew members

At present, various radio navigation systems are employed during the automated approach of a transport vehicle to a space station. Experience has shown that emergency situations can occur in which it is necessary to revert to manual override of the automatic approach.Such situations have indeed occurred during flight operations of the space station Mir. The crews of the transport vehicles and the Mir used manual steering more than 30 times for successful docking, and four times for approach to the station.Successful manual steering demands absolute understanding of the relative orbit parameters. The decisive task of the crew is to determine these relative parameters. This is possible using visual observations from either the transport vehicle or the station using simple and reliable instruments. This article explains the algorithm for determining the relative orbits from visual crew observations, based on similarities of relative orbit families.     

飞行器持续气动加热的耦合性分析

分析了飞行器持续受热过程中的耦合性，指出了耦合性在分要持续气动加热问题中的必要性。针对存在的耦合性，本文提出了一种处理方法，并在此基础上给出了部分模拟计算结果。这些结果能够定性地反映出耦合性在气动加热问题上的影响。同时指出，任何瞬态算法和技术在评估飞行器持续受热和导热问题时必须十分慎重。