现代管理方法应用于科研计划管理的研究分析

本文就有关现代管理方法的概念，价值以及应用作了阐述和分析，并结合企业实际情况进行企业采用现代管理技术的应用分析和建议。     

基于气象数据系留气球状态参数计算

为分析系留气球在实际应用地气象条件下的系留状态，基于标准大气模型分别在标准大气和实际气象测量的参数下对系留气球主要状态参数重量、重心、0风速平衡俯仰角进行计算。结果表明，应用实际气象数据参数计算的结果会在标准大气计算结果的基础上呈现波动变化。通过不断积累气象数据，利用系留气球实际应用地气象参数计算可对后续系留气球设计进行指导，使系留气球更好地在任务地点使用。     

小波分析在航空发动机性能趋势监控中的应用

简要分析了小波变换的原理、应用和算法。利用MATLAB编程，初步探讨了小波分析在发动机性能监控方面的应用。最后，通过实际的发动机数据对这种方法进行了验证，并对结果和应用前景进行了讨论。     

END-FIRE下滑天线系统在九寨黄龙机场的应用分析

本文从九寨黄龙机场国内首次应用END-FIRE下滑天线系统的实际背景出发，概括论述了该天线系统的国外应用、验证情况和系统组成，分析了该天线系统的原理，研究分析该天线系统的优势和劣势及应用前景。     

专用工具管理系统的开发及应用

阐述了专用工具的管理职能及其特点，分析了应用计算机辅助管理技术的重要性，介绍了公司开发的专用工具管理系统及其实际应用效果，提出了系统的发展方向。     

西门子SIMODRIVE 610驱动系统6SC64X0-0TE01模板的维修

西门子的驱动系统广泛的应用在我公司的数控设备上，本文针对西门子610驱动模板的常见故障，根据实际维修情况和实际测绘模板图纸，简单分析西门子驱动模块的工作原理和故障排除方法。     

选择先进的材料分析方法，提升应用技术价值

材料分析方法是进行应用技术分析重要的基本手段之一。结合公司科研生产实际情况介绍了一些先进的材料分析方法及应用的特点，提出了一些在解决工艺技术难点问题时应如何进行分析的基本思路，为公司合理选择有效分析手段和提升应用技术价值提供参考依据。     

寻求提高火箭发动机推力和比冲的新途径──环形喷管应用探讨

对环形喷管的概念、特性、分类及其应用作了详细说明，介绍了国内外环形喷管的研究概况，并分析了环形喷管在实际应用中会遇到的问题及解决方法。     

贯彻《测量不确定度表示指南》须研究解决的几个问题

为了科学地、合理地应用测量不确定度表示方法，必须研究解决一些急待解决的问题，发测量不确家原理的实际应用问题，测量误差的概率分布和性质，动态测量不确定度的分析与评定。误差修正技术的研究和应用等。     

基于准贝叶斯结构的决策融合

证据理论是目前在决策融合技术中受到广泛重视的一种数学方法。在实际应用中，为了表达简洁和计算简单，常常根据准贝叶斯结构进行判断。本文系统阐述这一过程的一般性步骤，并通过实际问题进行分析。     

New battery types for space vehicles

Engineers from all over the world came to discuss their new developments at the 36^th Intersociety Energy Conversion Engineering Conference (IECEC), held in Savannah, Georgia, USA, July 30 through August 2, 2001. Twenty battery presentations covered topics ranging from powering instruments in oil-well boreholes to supplying energy to instruments on the surface of Mars. Important developments in aerospace batteries are summarized in this article     

The High Energy Telescope for STEREO

The IMPACT investigation for the STEREO Mission includes a complement of Solar Energetic Particle instruments on each of the two STEREO spacecraft. Of these instruments, the High Energy Telescopes (HETs) provide the highest energy measurements. This paper describes the HETs in detail, including the scientific objectives, the sensors, the overall mechanical and electrical design, and the on-board software. The HETs are designed to measure the abundances and energy spectra of electrons, protons, He, and heavier nuclei up to Fe in interplanetary space. For protons and He that stop in the HET, the kinetic energy range corresponds to ～13 to 40 MeV/n. Protons that do not stop in the telescope (referred to as penetrating protons) are measured up to ～100 MeV/n, as are penetrating He. For stopping He, the individual isotopes ³He and ⁴He can be distinguished. Stopping electrons are measured in the energy range ～0.7–6 MeV.     

The IMPACT Solar Wind Electron Analyzer (SWEA): Reconstruction of the SWEA Transmission Function by Numerical Simulation and Data Analysis

The IMPACT SWEA instruments on board the twin STEREO spacecraft detect the solar wind electrons with energies between 1 and 2000 eV. The instruments provide 3-dimensional velocity distributions, pitch angle distributions and solar wind properties at two vantage points in the ecliptic at 1 AU. A few days after launch suppression of the low energy solar wind electrons was detected, which makes data analysis challenging and causes a significant loss of information below 50 eV. This paper describes the methods used to both understand the nature of the problem and to recover the most information about the low energy solar wind electrons from the measured datasets. These include numerical simulations, in-flight calibration results, and data reconstruction methods that allow the calculation of solar wind parameter proxies with minor limitations.     

Atmosphere-magnetosphere-ionosphere system mami

The effects on the terrestrial atmosphere and ionosphere of energy and momentum sources of magnetospheric origin are investigated theoretically. Parameters measured by instruments on board the GGS spacecraft and by the GGS ground-based networks are used as inputs to the models that quantify the magnetosphere-ionosphere-thermosphere coupling. Images of the aurora acquired at ultraviolet, visible and X-ray wavelengths by instruments on board the POLAR spacecraft are particularly useful in this investigation by yielding good spatial coverage and high time resolution of the aurora.The National Center for Atmospheric Research is sponsored by the National Science Foundation.     

The Jupiter Energetic Particle Detector Instrument (JEDI) Investigation for the Juno Mission

The Jupiter Energetic Particle Detector Instruments (JEDI) on the Juno Jupiter polar-orbiting, atmosphere-skimming, mission to Jupiter will coordinate with the several other space physics instruments on the Juno spacecraft to characterize and understand the space environment of Jupiter’s polar regions, and specifically to understand the generation of Jupiter’s powerful aurora. JEDI comprises 3 nearly-identical instruments and measures at minimum the energy, angle, and ion composition distributions of ions with energies from H:20 keV and O: 50 keV to >1 MeV, and the energy and angle distribution of electrons from <40 to >500 keV. Each JEDI instrument uses microchannel plates (MCP) and thin foils to measure the times of flight (TOF) of incoming ions and the pulse height associated with the interaction of ions with the foils, and it uses solid state detectors (SSD’s) to measure the total energy (E) of both the ions and the electrons. The MCP anodes and the SSD arrays are configured to determine the directions of arrivals of the incoming charged particles. The instruments also use fast triple coincidence and optimum shielding to suppress penetrating background radiation and incoming UV foreground. Here we describe the science objectives of JEDI, the science and measurement requirements, the challenges that the JEDI team had in meeting these requirements, the design and operation of the JEDI instruments, their calibrated performances, the JEDI inflight and ground operations, and the initial measurements of the JEDI instruments in interplanetary space following the Juno launch on 5 August 2011. Juno will begin its prime science operations, comprising 32 orbits with dimensions 1.1×40 RJ, in mid-2016.     

Validation of techniques for space based remote sensing of auroral precipitation and its ionospheric effects

Knowledge of the spatial distribution of auroral precipitation and its associated ionospheric effects is important both to scientific studies of the Earth's environment and successful operation of defense and communication systems. Observations with the best spatial and temporal coverage are obtained through remote sensing from space-based platforms. Various techniques have been used, including the detection of visible, ultraviolet and X-ray emissions produced by the precipitating particles. Interpretation of the measurements is enabled through theoretical modeling of the interaction of precipitating particles with atmospheric constituents. A great variety of auroral precipitation exists, with each kind differing in the type and energy distribution of the particles, as well as in its spatial and temporal behavior. Viable remote sensing techniques must be able to distinguish at least the species of particle, the total energy flux, and the average energy. Methods based on visible, ultraviolet and X-ray emissions meet these requirements to varying degrees. These techniques and the associated space instrumentation have evolved in parallel over the last two decades. Each of the methods has been tested using simultaneous measurements made by space-based imaging systems and ground-based measurements made by radars and optical instruments. These experiments have been extremely helpful in evaluating the performance and practicality of the instruments and the results have been crucial in improving instrument design for future remote sensing platforms. The next decade will see continued development and test of remote sensing instruments and the measurements, in addition to providing important operational data, will be increasingly more critical in addressing a number of scientific problems in auroral and atmospheric physics.     

X-ray emission from cataclysmic variables

EXOSAT results on cataclysmic variables are reviewed. The long continuous X-ray observations afforded by this observatory, coupled with the sensitivity of its instruments to medium energy and very low energy X-rays, have enabled the rotational and orbital X-ray light curves of these stars to be measured in unprecedented detail. Examples are given of data on synchronously and asynchronously rotating magnetic systems, and on disc accreting stars. The impact of the new observations on our understanding of cataclysmic variables is discussed.     

The Magnetic Electron Ion Spectrometer (MagEIS) Instruments Aboard the Radiation Belt Storm Probes (RBSP) Spacecraft

This paper describes the Magnetic Electron Ion Spectrometer (MagEIS) instruments aboard the RBSP spacecraft from an instrumentation and engineering point of view. There are four magnetic spectrometers aboard each of the two spacecraft, one low-energy unit (20–240 keV), two medium-energy units (80–1200 keV), and a high-energy unit (800–4800 keV). The high unit also contains a proton telescope (55 keV–20 MeV). The magnetic spectrometers focus electrons within a selected energy pass band upon a focal plane of several silicon detectors where pulse-height analysis is used to determine if the energy of the incident electron is appropriate for the electron momentum selected by the magnet. Thus each event is a two-parameter analysis, an approach leading to a greatly reduced background. The physics of these instruments are described in detail followed by the engineering implementation. The data outputs are described, and examples of the calibration results and early flight data presented.