一种气浮模拟器位姿状态跟踪测量方法研究

气浮模拟器为了模拟空间飞行器在地面状态的姿态运动和轨道机动运动，需要在大平面空间和大角度空间范围内运动。运动控制和实际运动位置和姿态形成闭环控制，需要一种在超大平面空间范围内快速测量位置和姿态的测量方法和策略，从而提供高精度闭环控制。用iGPS和惯导同步测量模拟器的位置和姿态，通过飞轮和冷气喷嘴伺服动作，实现了气浮模拟器的位置和姿态跟踪，可以广泛应用于其他超大尺度空间位置和姿态测量跟踪。     

带锥口圆柱内锥腔的发射率

用斯托克斯理论和曲线积分,推导了在漫散发射和反射假设下,均匀和非均匀带锥口圆柱内锥腔的逐点有效发射率分布和积分腔发射率的计算方法和公式。其结果己用于点源黑体的腔型选择和有效发射率的计算。     

全球军火商云集阿布扎比国际防务展

阿布扎比防务展是中东和北非地区唯一的海陆空三军装备展,也是国际上最大规模的防卫展之一。中东地区强劲的经济实力、特殊的地理位置和迫切的军备购买需求,阿联酋开放的心态和与东西方、穆斯林国家多方位的密切关系吸引了全球绝大多数的军火生产商、销售公司和各国政要、军队高级官员参展和参观。     

基于CAN总线的控制系统地面仿真测试平台研究

针对采用CAN总线进行数据传输的小卫星和运载火箭控制系统开展地面仿真测试评估研究。基于CAN总线和以太网构成总线网络,构建卫星和运载火箭控制系统地面仿真测试评估平台,给出总线上各仿真节点和实物节点的软硬件设计方案,设计了机内测试模拟方案。仿真验证分析表明,利用该平台可以对卫星和运载火箭控制系统信号、总线运行情况、控制周期和网络时延等进行正确分析,为卫星和运载火箭控制系统方案评估、控制方法和快速测试方法研究等提供理论依据和技术支持。     

星系和宇宙

从古到今,人们一直对太空中的星星充满着好奇,并渴望了解和认识它。此外,今天的社会要求人们打开狭窄的眼界,从各种不同的途径汲取知识和丰富自己;纵观人类历史的发展,认识星系和宇宙,除了能够丰富知识之外,它还能够影响到一个人的思维方式,甚至人生观,所以了解星系和宇宙是非常必要的。鉴于很多人渴望了解这方面知识,但又没有时间和精力去阅读那些厚厚的天文书籍,本文以连载的方式、采用提问的形式和图文并茂的模式,围绕着"星系和宇宙"这个主题,介绍关于太阳系、银河系、河外星系以及宇宙探测技术等问题,让读者和宇宙对话。     

心与火箭一起飞

我敢断言,《天歌》的作者和绝大多数人肯定没有亲身体验过飞向太空的那种天旋地转,江河倒流,时空错乱的滋味。然而,天泉和建明却走进我国导弹基地以及几代火箭人的身旁,用深情,用激情,用大脑和文字真实地记录和见证了那些神秘和神奇的故事。     

航天器初始飞行段雷测系统误差估计方法与算法

在航天器初始飞行段的跟踪数据中,假设光测数据含有常值系统误差,连续波雷达系统的距离和／差数据含有二次项系统误差和折射残差,距离和／差变化率数据含有线性系统误差和折射残差。利用样条函数表示轨道,建立了系统误差和航天器轨道的非线性模型,给出了系统误差和轨道的高精度估计方法和算法。     

《空间控制技术与应用》选题大纲

<正>一、总体设计1.系统理论、系统工程、系统集成与一体化设计2.控制系统方案设计3.先进的控制理论和方法(自适应控制、智能控制、鲁棒控制、模糊控制、变结构控制、最优控制等)4.系统建模、系统辨识和状态估计二、制导、导航与控制1.自主导航与组合导航技术2.姿态动力学和轨道动力学3.姿态测量和姿态确定技术4.挠性结构动力学和控制5.姿态控制和轨道控制6.交会对接与返回再入技术     

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。     

数据库结构和数据的转换方法

介绍了如何把微机上的关系型数据库结构和数据转换成UNISYS 2200401机及MAPPER 上的数据库和数据的转换程序,主要介绍实现方法、设计思想、技术上实现途径和难点,以及系统构成和系统功能。     

嫦娥三号“玉兔号”巡视器行为规划方法

为支持"玉兔号"巡视器完成对月面较大空间范围的科学探测,对动态任务进行快速规划,提出了一种基于人工智能领域智能规划技术的自动化任务规划方法。提出了行为持续时间和行为效果动态确定的时态规划模型(TP~(DDDE)),设计了描述TP~(DDDE)问题的规划领域定义语言PDDL——PDDL~(DDDE),以及针对TP~(DDDE)问题的启发式规划算法,运用Landmark知识分析规划问题结构,从而设计了合理反映动作前提评估顺序的启发函数。在嫦娥三号任务中,本文方法支撑"玉兔号"巡视器圆满完成了预期的科学探测任务。     

THE SPACE APPLICATION ACHIEVEMENTS OF THE CHINESE UNMANNED SPACECRAFT "SZ-3"

During the 3rd mission of Chinese Unmanned Spacecraft the application sys tem of "SZ-3" (Shenzhou, a divine ship) gets a great success, all its goals are achieved. Many areas of science and breakthrough technology, including earth observation, earth environment monitoring, space material, space life science etc., are carried out in the mission. There are 44 payload instruments totally.All the instruments are working well during the orbit flight and a lot of good results are obtained. Many areas, for example the moderate resolution imag ing spectroradiometer, the solar ultraviolet spectral irradiance monitor and the space protein crystallization facility perform better than required and expected.A brief introduction of the experiments and the achievements of the mission is given in this paper.     

陀螺用H型动压气浮轴承电机启动特性

为满足卫星长寿命应用的需求,H型动压气浮轴承在陀螺上得到了应用.在应用过程中,对其有了更深刻的认识.首先介绍动压气浮轴承的基本结构及原理,然后对H型动压气浮轴承不同姿态下的启动特性进行详尽地分析,并给出研究结果及启示.     

The Spacelab-Mir-1 "Greenhouse-2" experiment.

The Spacelab-Mir-1 (SLM-1) mission is the first docking of the Space Shuttle Atlantis (STS-71) with the Orbital Station Mir in June 1995. The SLM-1 "Greenhouse-2" experiment will utilize the Russian-Bulgarian-developed plant growth unit (Svet). "Greenhouse-2" will include two plantings (1) designed to test the capability of Svet to grow a crop of Superdwarf wheat from seed to seed, and (2) to provide green plant material for post-flight analysis. Protocols, procedures, and equipment for the experiment have been developed by the US-Russian science team. "Greenhouse-2" will also provide the first orbital test of a new Svet Instrumentation System (SIS) developed by Utah State University to provide near real time data on plant environmental parameters and gas-exchange rates. SIS supplements the Svet control and monitoring system with additional sensors for substrate moisture, air temperature, IR leaf temperature, light, oxygen, pressure, humidity, and carbon-dioxide. SIS provides the capability to monitor canopy transpiration and net assimilation of the plants growing in each vegetation unit (root zone) by enclosing the canopy in separate, retractable, ventilated leaf chambers. Six times during the seed-to-seed experiment, plant samples will be collected, leaf area measured, and plant parts fixed and/or dried for ground analysis. A second planting initiated 30 days before the arrival of a U.S. Shuttle [originally planned to be STS-71] is designed to provide green material at the vegetative development stage for ground analysis. [As this paper is being edited, the experiment has been delayed until after the arrival of STS-71.]     

Upgrading CCIR's foF2 maps using available ionosondes and genetic algorithms

We have developed a new approach towards a new database of the ionospheric parameter $f_{o}F2$. This parameter, being the frequency of the maximum of the ionospheric electronic density profile and its main modeller, is of great interest not only in atmospheric studies but also in the realm of radio propagation. The current databases, generated by CCIR (Committee Consultative for Ionospheric Radiowave propagation) and URSI (International Union of Radio Science), and used by the IRI (International Reference Ionosphere) model, are based on Fourier expansions and have been built in the 60s from the available ionosondes at that time. The main goal of this work is to upgrade the databases by using new available ionosonde data. To this end we used the IRI diurnal/spherical expansions to represent the $f_{o}F2$ variability, and computed its coefficients by means of a genetic algorithm (GA). In order to test the performance of the proposed methodology, we applied it to the South American region with data obtained by RAPEAS (Red Argentina para el Estudio de la Atmósfera Superior, i.e. Argentine Network for the Study of the Upper Atmosphere) during the years 1958–2009. The new GA coefficients provide a global better fit of the IRI model to the observed $f_{o}F2$ than the CCIR coefficients. Since the same formulae and the same number of coefficients were used, the overall integrity of IRI’s typical ionospheric feature representation was preserved. The best improvements with respect to CCIR are obtained at low solar activities, at large (in absolute value) modip latitudes, and at night-time. The new method is flexible in the sense that can be applied either globally or regionally. It is also very easy to recompute the coefficients when new data is available. The computation of a third set of coefficients corresponding to days of medium solar activity in order to avoid the interpolation between low and high activities is suggested. The same procedure as for $f_{o}F2$ can be perfomed to obtain the ionospheric parameter M(3000)F2.     

某型歼击机座舱盖"零-零"抛放轨迹计算研究

建立了某型歼击机座舱盖"零-零"抛放过程的运动模型,得到了座舱盖抛放过程的空间运动轨迹和最佳抛放角,计算结果与试验测量结果相符.同时还研究了抛盖动作筒的进气规律,得到了抛盖动作筒下腔的进气流量及压力随时间的变化曲线,从而预测了座舱盖抛放过程的空间运动轨迹.      

关于北斗卫星导航系统的被动式定位算法比较研究

我国北斗卫星导航系统空间卫星共有2或3颗,无法单独满足被动导航定位的要求．针对这种卫星稀少的情况提出了3种被动式定位算法: 2星定位算法、 3星3参数定位算法和3星4参数定位算法, 这些算法分别采用气压测高方法增加观测数据和采用数学模型描述接收机钟差的方法减少定位方程求解的未知数;探讨了北斗卫星导航系统备份星的可用性和对导航定位精度的贡献;还提出了准差分修正技术,提高了定位精度．实验证明, 3种算法都取得了100m以内的定位结果,可以满足一般用户定位需求．     

Real-time spacecraft intercept strategy on J2-perturbed orbits

A real-time intercept strategy for spacecraft under the non-uniform gravitational perturbation of Earth is addressed in this paper. To intercept a target spacecraft on general conic sections, an interceptor considered in this work makes use of a thruster propelling the constant thrust which is comparable to unrealistic impulse-type thrust. The $J_2$ perturbation introduces critical dynamic variations of spacecraft orbiting the Earth, which results in a considerable amount of position error of the interceptor at the final intercept point. In order to release the burden of $J_2$ disturbance and make the miss distance between the target and interceptor small, a real-time intercept technique with an optimal intercept algorithm is suggested. The strategy proposed is to obtain an optimized output iteratively for a given time interval with previously obtained optimal values. These parameters are evaluated by the optimal intercept algorithm suggested. Once the optimal velocity change is obtained to satisfy intercept requirements, although the orbital system is perturbed, it is easy to regenerate a new solution by setting the previous solution as new initial guesses. This strategy is employed iteratively until the interceptor meets the target. Several numerical simulations are performed to highlight the proposed real-time strategy for spacecraft intercept missions.     

Microgravity effects on "postural" muscle activity patterns.

Changes in neuromuscular activation patterns associated with movements made in microgravity can contribute to muscular atrophy. Using EMG to monitor "postural" muscles, it was found that free floating arm flexions made in microgravity were not always preceded by neuromuscular activation patterns normally observed during movements made in unit gravity. Additionally, manipulation of foot sensory input during microgravity arm flexion impacted upon anticipatory postural muscle activation.     

“8785”返地卫星搭载对卤虫卵发育影响的研究

将我国所产卤虫(Artemia salina)的卵,由1987年8月5日发射的返地卫星搭载,在空间飞行5天。于飞行完成后第8、21、24、34及66天,随机取卵进行人工孵化及发育观察。见到的主要现象有:(1)飞行卵的早期发育进程显著变慢;(2)随着回收后时间的延长,飞行卵的早期发育速度出现回升的趋势;(3)飞行卵早期发育中的冒出率和孵出率一般都比地面对照组的低,且随着回收后时间的延长,有继续下降的趋势;(4)飞行卵孵出的卤虫,自孵出第1天至接近全部自然死亡的23天内,存活率的下降情况与地面对照组的没有差异。本文提出一种空间飞行因素对卤虫卵损伤的“临界程度”的假设。实验还表明,我国所产的卤虫卵对空间飞行因素的作用是敏感的,是一种空间生物学研究的好材料。