On the stability of the track of the space elevator

A string moving with geostationary angular velocity in its radial relative equilibrium configuration around the Earth, reaching from the surface of the Earth far beyond the geostationary height, could be used as track for an Earth to space elevator. This is an old dream of mankind, originating about 100 years ago in Russia. Besides the question of feasibility from a technological point of view also the question concerning the stability of such a configuration has not yet been completely solved. Under the assumption that a proper material (carbon nanotubes) is available, making the connection possible technologically, we address the question of existence and stability of the radial relative equilibrium of a tapered string on a circular geosynchronous trajectory around the Earth, reaching from the surface of the Earth far beyond the geostationary height.     

On the Possibility of the Existence of Volatile Compounds in the Region of the Scott Crater on the Moon

In this paper, we analyze the illumination conditions, the thermal regime, and the possibility of deposits of volatile compounds existing in the vicinity region (NSR S5 region) near the southern pole of the Moon. It has been found that there are no permanently shadowed zones near the Scott crater and the NSR S5 region, though the temperature conditions allow the of compounds such as CH₃OH, SO₂, NH₃, CO₂, H₂S, C₂H₄, and water to remain stable relative to evaporation for a long time (≥1 Gyr). It has been also shown that compounds like CO and CH₄ cannot stably exist in these regions.     

Estimation of the current density and analysis of the geometry of the current system surrounding the Earth

The results of an investigation of the distribution of plasma pressure, pressure gradients, and magnetic field near the equatorial plane in the plasma ring surrounding the Earth under magneto-quiet conditions are presented. Observational data obtained during the international THEMIS mission are used. The picture of the distribution of transverse-current density near the equatorial plane was obtained under assumption of observing the magnetostatic balance condition at geocentric distances from 6 to 12R _E. In estimating the integral transverse current it was accepted that in daytime sector the magnetic-field minima on magnetic field lines are not localized in the equatorial plane. Estimates of the integral transverse current were obtained, which demonstrate the possibility of closing nighttime transverse currents at geocentric distances of up to ～12R _E inside the magnetosphere, which form a high-latitudinal continuation of the ring current.     

Estimating the accuracy of the technique of reconstructing the rotational motion of a satellite based on the measurements of its angular velocity and the magnetic field of the Earth

The paper has studied the accuracy of the technique that allows the rotational motion of the Earth artificial satellites (AES) to be reconstructed based on the data of onboard measurements of angular velocity vectors and the strength of the Earth magnetic field (EMF). The technique is based on kinematic equations of the rotational motion of a rigid body. Both types of measurement data collected over some time interval have been processed jointly. The angular velocity measurements have been approximated using convenient formulas, which are substituted into the kinematic differential equations for the quaternion that specifies the transition from the body-fixed coordinate system of a satellite to the inertial coordinate system. Thus obtained equations represent a kinematic model of the rotational motion of a satellite. The solution of these equations, which approximate real motion, has been found by the least-square method from the condition of best fitting between the data of measurements of the EMF strength vector and its calculated values. The accuracy of the technique has been estimated by processing the data obtained from the board of the service module of the International Space Station (ISS). The reconstruction of station motion using the aforementioned technique has been compared with the telemetry data on the actual motion of the station. The technique has allowed us to reconstruct the station motion in the orbital orientation mode with a maximum error less than 0.6° and the turns with a maximal error of less than 1.2°.     

实施“三位一体”教育模式 提高学生的综合素质

本文介绍了“三位一体”教育模式的内容,描述亍我们实施该模式所采取的措施及取得的成效。实践表明,“三位一体”教育模式能够提高学生的综合素质,为学生毕业后的发展打下坚实基础,对教育模式的改革具有一定的指导意义。     

Optimization of the trajectory of the spacecraft insertion into the system of heliocentric orbits

The possibility of the spacecraft insertion into the system of operational heliocentric orbits has been analyzed. It has been proposed to use a system of several operational heliocentric orbits. On each orbit, the spacecraft makes one or more revolutions around the Sun. These orbits are characterized by a relatively small perihelion radius and relatively high inclination, which allows one to investigate the polar regions of the Sun. The transition of the spacecraft from one orbit to another has been performed using an unpowered gravity assist maneuver near Venus and does not require the cruise propulsion operation. Each maneuver transfers the spacecraft into the sequence of operational heliocentric orbits. We have analyzed several systems of operational heliocentric orbits into which the spacecraft can be inserted by means of the considered transportation system with electric propulsion (EP). The mass of the spacecraft delivered to these systems of operational orbits has been estimated.     

从应变计现状看电阻式传感器的前景

电阻式传感器的核心部件——电阻应变计是目前最常用的应力分析的敏感元件。也常用于测量力、压力、扭矩和加速度等物理量。作者简要回顾了电阻应变计的发展历史，介绍了电阻应变计的结构、分类及现状，展望了电阻式传感器的前景。     

System of works on numerical modeling of the dynamics of the structure of the Space Radiotelescope in the RadioAstron project

The results of modeling the dynamics of the Space Radiotelescope are presented. The results of ground-based vibration-dynamic tests are used to validate the calculation models and estimate the damping levels. The dynamic distortions of the reflecting surface caused by the operation of the pointing mechanism of the high-gain antenna are estimated.     

火箭推进剂液体晃动关机响应的数值仿真

本文采用VOF方法对火箭发动机关机阶段所引起的液体晃动进行了数值仿真，以氧化剂贮箱为例，得到了贮箱无阻尼环和带阻尼环时的晃动仿真图和液体质心变化曲线，检验了VOF方法处理碎波的能力。     

信道相关性对分集合并接收性能的影响

简介分集接收的主要方式 ,定量分析信道相关性对分集接收性能的影响。特别针对 Rayleigh信道模型中最大比合并和选择合并在各分集支路相关时的性能作了仔细研究 ,给出仿真结果 ,验证各分集支路相关性越小 ,分集效果越好的结论。在最大比合并下 ,当各路平均信噪比与门限相比较小时 ,各分集支路越相关 ,输出信噪比超过门限的概率越大。     

大学生诚信缺失的对策探讨

诚信是中华民族的传统美德，是社会生活正常运行的道德基础，是市场经济有序发展的基本要素，是和谐社会构建的重要标尺。但近年来，在大学生无视诚信的现象不容忽视。为此要发扬传统文化之精髓，弘扬当代大学生的诚信精神，并且实行知行统一。     

Stochastic Correlation Models for the Motion of the Pole of the Deformable Earth

In this paper we develop an unconventional approach to investigations of possible stochastic phenomena in the rotational motions of celestial bodies. The approach is based on special equations of the rotational motion, which represent a three-dimensional nonlinear system of differential equations with random parameters.     

人为本中不能解读为以人民为本

以人为本思想内涵丰富，以人民为本是以人为本的种概念；“人”和“人民”各有其特定的涵义；在内涵上，“人”要比“人民”更丰富，在外延上，“人”要比“人民”宽泛得多；在中国现阶段，就落实以人为本来看，也有其特定的要求和针对性。因此，人为本中不能解读为以人民为本。     

On the assurance of the design accuracy of the space radio telescope RadioAstron

The results are given of the theoretical calculations and the results of measurements of the shape of the reflecting surface of the space telescope conducted during the manufacture of individual elements and assembly of the product as a whole.     

硅集成电路老炼时间确定和寿命预计

文章基于阿列纽斯经验公式,利用相关标准中的数据,拟合得到硅集成电路老炼试验温度和时间的关系,根据这种关系可以确定在标准未规定的高温下硅集成电路的老炼时间,同时预计了硅集成电路的工作寿命。最后基于经典的温度应力加速试验模型进行了分析,并与前者进行了对比。     

金属膜片贮箱推进剂消耗不平衡分析

分析了某型号推进系统金属膜片贮箱推进剂消耗不平衡问题,建立了不平衡消耗的计算模型,对地面排放试验和飞行时系统推进剂消耗不平衡量进行了计算。并通过地面试验对计算数据进行了比较。结果表明,根据系统的静态计算模型,给定影响因素偏差来确定推进剂消耗不平衡的计算方法正确、有效。     

飞行器外部电磁环境分析与辐射安全裕度试验方法研究

辐射安全裕度是系统级电磁兼容性的关键指标,是保证系统能够在使用环境下正常工作的前提。从安全裕度的定义出发,分析外部电磁环境对于系统安全裕度的重要意义,指出现有辐射安全裕度试验方法的缺陷。提出用于评估外部电磁环境的两种方法,并指出考虑外部电磁环境后辐射安全裕度测试的难点。文中还分析了系统对外部电磁环境的感应特性,提出一种新的辐射安全裕度测试方法,降低了测试难度,使安全裕度测试更加全面、有效。     

Drying as one of the extreme factors for the microflora of the atmosphere

An investigation of the effects of drying and drying-rewetting cycles under vacuum conditions of 10(-2) torr at -30 degrees C on conidia of the atmospheric strain Penicillium chrysogenum from 48-77 km heights, collected by meteorological rockets found that survival and restoration of the initial physiological properties were possible through some very efficient protective cellular mechanisms. Such adaptive possibilities explain the widespread diffusion of microbial cells throughout the biosphere of our planet.     

光学遥感器整体优势突显中巴地球资源卫星的特色

中巴地球资源卫星高层技术决策立足两个发展中国家的具体国情，着眼于自身整体优势和国际应用，根据国际地球资源卫星发展趋势和客观规律，准确地把握了中巴地球资源卫星技术发展方向。科学合理地进行了多谱段及其不同分辨率的遥感器配置，使中巴地球资源卫星多种有效载荷技术性能和指标互补，综合技术指标先进，光学遥感器技术指标整体优势已经突显出中巴地球资源卫星的特色，瞻望发展前景遥感器技术水平将明显提高，卫星应用范围将日趋扩大。     

Results of the early orbit manoeuvres of the ampte-uks

The Active Magnetospheric Particle Tracer Explorers (AMPTE) program consists of three satellites which were launched on 16th August 1984. The scientific aim of the mission is to inject lithium and barium tracer ions inside and outside the Earth's magnetosphere and to detect and monitor these ions as they diffuse through the inner magnetosphere. The first of these three satellites, the U.S. Charge Composition Explorer (CCE) was launched into an elliptical orbit of apogee 8 R_e. The other two satellites are the West German Ion Release Module (IRM) and the U.K. Subsatellite (UKS), both of which were launched on the same vehicle into a highly elliptical orbit of apogee 18 R_e. At discreet intervals during the mission the IRM will release ions into the solar wind, and the movement of these ions will be monitored by the UKS. Depending on the particular scientific requirement, the UKS has to be positioned accurately at a given distance behind the IRM. Initially the UKS has to be located 100 km behind the IRM, and held there for ～9 months. It will then be moved a distance of ～1 R_e behind the IRM. In order to manoeuvre the UKS around its orbit, a cold gas jet system is incorporated on the satellite, allowing impulses to be applied both along and perpendicular to the orbit velocity vector. The orbit control system also has to cater for relative orbit changes due to air drag at perigee, as the IRM and the UKS have different $\text{area}\text{mass}$ ratios. This paper presents an account of the orbit control system implemented on the UKS, together with the mathematical approach adopted, and results from manoeuvres made in the first weeks of the mission.