高可靠三冗余伺服机构系统

回顾了载人航天高可靠伺服机构系统的研制历程,介绍了载人航天运 载火箭三余度伺服机构系统原理、性能特点及其可靠性验证结果。     

载人航天器电动兼手动舱门的研究

为了适应载人航天出舱活动和交会对接技术的发展,需要研究一种既能在轨保持良好密封性能、又能实现电动兼手动操作的高可靠舱门机构。在分析了载人航天器舱门特点的基础上,提出了一种新型电动兼手动操作的舱门锁紧与开锁机构方案,设计了电动/手动切换机构,借用Pro/E软件对各零件进行三维造型和装配,并通过ADAMS软件进行了舱门机构的运动学仿真。模装与仿真结果表明,该电动兼手动舱门能够实现其预期的运动,无结构干涉,具有操作简单、操作力小、传动效率高的特点。     

Electrostatic space radiation shielding

For the success of NASA’s new vision for space exploration to Moon, Mars and beyond, exposures from the hazards of severe space radiation in deep space long duration missions is ‘a must solve’ problem. The payload penalty demands a very stringent requirement on the design of the spacecrafts for human deep space missions. The exploration beyond low Earth orbit (LEO) to enable routine access of space will require protection from the hazards of the accumulated exposures of space radiation, Galactic Cosmic Rays (GCR) and Solar Particle Events (SPE), and minimizing the production of secondary radiation is a great advantage. There is a need to look to new horizons for newer technologies. The present investigation revisits electrostatic active radiation shielding and explores the feasibility of using the electrostatic shielding in concert with the state-of-the-art materials shielding and protection technologies. The full space radiation environment has been used, for the first time, to explore the feasibility of electrostatic shielding. The goal is to repel enough positive charge ions so that they miss the spacecraft without attracting thermal electrons. Conclusions are drawn for the future directions of space radiation protection.     

A small mission for in situ exploration of a primitive binary near-Earth asteroid

We present a concept for a challenging in situ science mission to a primitive, binary near-Earth asteroid. A sub-400-kg spacecraft would use solar electric propulsion to rendezvous with the C-class binary asteroid (175706) 1996 FG3. A campaign of remote observations of both worlds would be followed by landing on the ∼1 km diameter primary to perform in situ measurements. The total available payload mass would be around 34 kg, allowing a wide range of measurement objectives to be addressed. This mission arose during 2004 from the activities of the ad-hoc Small Bodies Group of the DLR-led Planetary Lander Initiative. Although the particular mission scenario proposed here was not studied further per se, the experience was carried over to subsequent European asteroid mission studies, including first LEONARD and now the Marco Polo near-Earth asteroid sample return proposal for ESA’s Cosmic Vision programme. This paper may thus be of interest as much for insight into the life cycle of mission proposals as for the concept itself.     

国外载人航天器故障诊断技术

详细介绍了故障诊断技术在国外载人航天器故障诊断中的应用及发展过程，并对专家系统技术进行了重点分析和介绍，国外载人航天器故障诊断经历了60年代简单的状态监测（水星号），70年代的基于算法的诊断（阿波罗），一直到80年代的基于知识的智能诊断（航天飞机），三个阶段，还介绍了NASA为其航天飞机主发动机透平泵和空间站电源系统开发的故障诊断专家系统，并对航天领域故障诊断技术特点进行了综合分析，同时指出了航天领域故障诊断技术的发展趋势。     

空间核反应堆电源技术概览

空间核反应堆电源具有环境适应性好、功率覆盖范围广、结构紧凑以及大功率条件下质量功率比小等突出优点,在军民航天任务中具有广阔的应用前景,是改变未来航天动力格局的颠覆性技术之一。对空间核反应堆电源的原理、特点、适用范围、应用前景、历史发展情况及现状、典型方案、应用安全等进行了系统介绍,对技术发展趋势进行了分析总结,并就我国该技术发展给出一些见解。     

载人航天着陆场选择与分析

根据载人航天的任务和特点,结合对着陆场的要求,从工程应用的角度出发,对中国载人航天着陆场进行了选择论证,并进行了综合分析;其正确性和可行性在多次无人飞行试验和两次载人飞行任务中得到实际考核和验证。     

任务可靠性指标分配的比例组合法及评分分配法

提出了一种工程化的任务可靠性指标分配的方法。分析了任务可靠性分配的实质,把适用于基本可靠性指标分配的比例组合法与评分分配法的原则拓广到任务可靠性指标的分配,提出了工程化的任务可靠性指标分配方法,给出了表格化、规范化的工作程序,并讨论了这种工程处理方法的精度、收敛性等特点。     

大推力液体火箭发动机研究

大推力火箭发动机是航天发展的基础,是国家高科技水平和综合国力的体现。分析了运载火箭主动力发展的现状和趋势,指出大推力液氧煤油发动机和液氧液氢发动机是发展方向和最佳组合。提出了我国重型运载火箭大推力液氧煤油发动机和液氧液氢发动机的总体方案和主要参数,研究了两种发动机的关键技术及其解决途径。这两种大推力发动机的研制,将为我国载人登月、深空探测等重大航天活动和空间利用提供动力支撑。     

多层月球模型的自转动力学与着陆探测

着重于寻找月核证据并将月核模型引入月球天平动理论中,探讨如何将多种空间探测技术应用于毫角秒精度的月球天平动观测,进而测定液态和固态月核参量。通过讨论多层月球的月球物理参数、流体核的几何与动力学椭率、松散黏滞的月幔,可获得月球相关详细信息与参量,这些参量对评估多层结构的月球自由天平动很重要。物理天平动的解析理论还可应用于未来多种月球工作中,期望在近代月球科学研究基础上能有进一步发展。