对欧空局轨道碎片模型的评价

文章评价了颗粒大于1cm的碎片模型,它包含大于10cm的一组粒子和介于1～10cm之间的粒子,它们是由空间暴露模拟得到的。接着讨论了尺寸范围介于0.1～10mm之间的小粒子束流。假定这些粒子主要是由小粒子与卫星碰撞产生的。这种碰撞主要发生在450～500kin的高度范围内(空间站高度),碰撞与否还取决于轨道高度和离心率。     

联盟TM交会对接的地面远程导引段制导方法分析与研究

就俄罗斯联盟TM 号飞船与和平号轨道空间站交会对接中的远距离接近段所报导的一些数据对其制导方法进行分析与研究。分析与计算结果表明, 采用固定时间燃料最省的四次冲量方法所获得的冲量大小、方向及冲量施加的时间与报导极为吻合     

超级电容器的电特性及在独立光伏系统中的应用

简要叙述了超级电容器的基本结构和工作原理，详细介绍了超级电容器的主要电参数和测试条件，分析了影响电特性的因素和机理，最后给出了超级电容器在独立光伏系统中的应用及注意事项。     

Debris flux comparisons from the Goldstone Radar,Haystack Radar,and Hax Radar prior,during, and after the last solar maximum

The continual monitoring of the low Earth orbit (LEO) debris environment using highly sensitive radars is essential for an accurate characterization of these dynamic populations. Debris populations are continually evolving since there are new debris sources, previously unrecognized debris sources, and debris loss mechanisms that are dependent on the dynamic space environment. Such radar data are used to supplement, update, and validate existing orbital debris models. NASA has been utilizing radar observations of the debris environment for over a decade from three complementary radars: the NASA JPL Goldstone radar, the MIT Lincoln Laboratory (MIT/LL) Long Range Imaging Radar (known as the Haystack radar), and the MIT/LL Haystack Auxiliary radar (HAX). All of these systems are highly sensitive radars that operate in a fixed staring mode to statistically sample orbital debris in the LEO environment. Each of these radars is ideally suited to measure debris within a specific size region. The Goldstone radar generally observes objects with sizes from 2 mm to 1 cm. The Haystack radar generally measures from 5 mm to several meters. The HAX radar generally measures from 2 cm to several meters. These overlapping size regions allow a continuous measurement of cumulative debris flux versus diameter from 2 mm to several meters for a given altitude window. This is demonstrated for all three radars by comparing the debris flux versus diameter over 200 km altitude windows for 3 nonconsecutive years from 1998 to 2003. These years correspond to periods before, during, and after the peak of the last solar cycle. Comparing the year to year flux from Haystack for each of these altitude regions indicate statistically significant changes in subsets of the debris populations. Potential causes of these changes are discussed. These analysis results include error bars that represent statistical sampling errors.     

编队卫星相对运动描述方法综述

对于近地轨道卫星编队飞行的相对运动理论研究,可以采用的方法包括直角坐标法和 轨道要素法。利用直角坐标法得到的相对运动动力学方程可以用于编队队形控制研究,轨道 要素法能够给出相对运动的运动学描述,便于定量研究摄动影响和进行编队队形设计。分析 了直角坐标法在描述卫星长期编队飞行方面的局限性,综述了利用轨道要素描述编队卫星相 对运动的各种研究方法,包括轨道要素差法、相对轨道要素法和参照轨道要素法等。     

区域观察小卫星星座重构方法研究

在对地观测任务中，经过优化设计的卫星星座通常具有较强的适应能力。但是，当星座中某颗卫星失效或地面需求发生变化时，就需要进行星座重构，以恢复或增强对部分地区的观察能力。提出了小卫星区域观察组网的方法，重点探讨了在应急情况下区域观察小卫星星座的重构问题，研究了节省能量的卫星轨道机动方法，特别提出了保持轨道属性和星座基本构形的预置量机动方法，分析了应急机动星座重构的几种情况，给出了每种情况的星座重构策略。     

KrF激光对高速飞片的驱动特性研究

利用诱导空间非相干技术平滑的KrF准分子（248nm）激光驱动带有烧蚀层的平面靶，研究激光空间均匀性对产生完整飞片的影响，结果表明激光不均匀性在2％以下，能够产生完整的高速飞片，且完整飞片能够维持20ns以上不破裂；当激光不均匀性达到5％，激光引入流体力学不稳定性种子应很强，冲击波在靶内输运过程中不稳定性不断发展增强，到靶背时强到足以使飞片解体甚至气化，不能产生完整的飞片。为了获得尽可能高的飞片速度，采用激光与烧蚀层参数不匹配方法，使冲击波对飞片作多次加速。利用功率密度为1012 W/cm2的KrF激光与含50μm Kapton烧蚀层的5μm铝飞片作用，得到速度约10km/s的高速飞片，与模拟结果吻合得很好。     

Investigation of national policy shifts to impact orbital debris environments

Low earth orbit has become increasingly congested as the satellite population has grown over the past few decades, making orbital debris a major concern for the operational stability of space assets. This congestion was highlighted by the collision of the Iridium 33 and Cosmos 2251 satellites in 2009. This paper addresses the current state of orbital debris regulation in the United States and asks what might be done through policy change to mitigate risks in the orbital debris environment. A brief discussion of the nature of orbital debris addresses the major contributing factors including size classes, locations of population concentrations, projected satellite populations, and current challenges presented in using post-mission active debris removal to mitigate orbital debris. An overview of the current orbital debris regulatory structure of the United States reveals the fragmented nature of having six regulating bodies providing varying levels of oversight to their markets. A closer look into the regulatory policy of these agencies shows that, while they all take direction from The U.S. Government Orbital Debris Mitigation Standard Practices, this policy is a guideline with no real penalty for non-compliance. Various policy solutions to the orbital debris problem are presented, ranging from a business as usual approach to a consolidated regulation system which would encourage spacecraft operator compliance. The positive aspects of these options are presented as themes that would comprise an effective policy shift towards successful LEO conservation. Potential economic and physical limitations to this policy approach are also addressed.     

地球静止卫星南北位置保持控制系统的选择

简述了地球静止卫星南北位置保持控制系统的要求，然后比较了化学推进和电推进控制系统的特点，并较具体地分析了几种典型的电火箭发动机的性能和发展水平。在此基础上提出了作者对地球静止卫星南北位置保持控制的选择原则和看法。     

一种空中交通图象特征匹配方法

提出了一种确定飞机类型的新方法。通过 机外型和结构特征，利用空间投影理论建立了飞机投影图形与飞机姿态角之间的关系。通过该关系方程，有效地识别了飞机姿态角。利用已有的飞机型的投影图特征与实际飞机飞行图像特征之间的误差，根据最小方差进行了模型匹配。利用ＣＣＤ系统图像仿真结果表明，所提出的方法是有效的。