排序方式: 共有31条查询结果,搜索用时 31 毫秒
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钝头体窄条翼布局导弹在大攻角下拥有极为优异的纵向气动特性,但横向容易失稳,做快速机动时容易诱发非指令的横向不稳定运动。通过开展高速风洞自由摇滚试验和数值模拟,研究了窄条翼导弹自由摇滚特性和流动机理,试验与计算吻合较好。研究发现:较大迎角时,窄条翼面积中心距离尾舵前缘根部5~6倍直径时,模型会进入极限环摇滚,窄条翼位置对模型稳定性有显著的影响,去掉窄条翼或尾舵时,模型均不会进入摇滚;模型空间流场特性表明,气流经过窄条翼时形成的片涡,对背风舵产生强烈的干扰,抑制了尾舵涡的形成和发展,使背风舵动态失稳,导致模型进入极限环摇滚。 相似文献
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文章从理论上计算了月球大气分子的逃逸率,解释了月球大气稀薄的原因。根据月岩和月壤放出的气体量与逃逸的气体量达到动态平衡的假定,说明了月球上大气密度昼夜的差异。 相似文献
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R.A. Mewaldt N.E. Yanasak M.E. Wiedenbeck A.J. Davis W.R. Binns E.R. Christian A.C. Cummings P.L. Hink R.A. Leske S.M. Niebur E.C. Stone T.T. Von Rosenvinge 《Space Science Reviews》2001,99(1-4):27-39
There are a number of radioactive clocks in the cosmic radiation that can be used to measure the time scales for cosmic ray processes in the Galaxy. With high-resolution isotope measurements available from ACE it is now possible to read these clocks with greatly improved accuracy and address key questions about the origin and lifetime of cosmic rays. This paper discusses the status of three such investigations. 相似文献
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M. E. Wiedenbeck W. R. Binns A. C. Cummings A. J. Davis G. A. de Nolfo M. H. Israel R. A. Leske R. A. Mewaldt E. C. Stone T. T. von Rosenvinge 《Space Science Reviews》2007,130(1-4):415-429
The galactic cosmic rays arriving near Earth, which include both stable and long-lived nuclides from throughout the periodic
table, consist of a mix of stellar nucleosynthesis products accelerated by shocks in the interstellar medium (ISM) and fragmentation
products made by high-energy collisions during propagation through the ISM. Through the study of the composition and spectra
of a variety of elements and isotopes in this diverse sample, models have been developed for the origin, acceleration, and
transport of galactic cosmic rays. We present an overview of the current understanding of these topics emphasizing the insights
that have been gained through investigations in the charge and energy ranges Z≲30 and E/M≲1 GeV/nuc, and particularly those using data obtained from the Cosmic Ray Isotope Spectrometer on NASA’s Advanced Composition
Explorer mission. 相似文献
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Stone E.C. Cohen C.M.S. Cook W.R. Cummings A.C. Gauld B. Kecman B. Leske R.A. Mewaldt R.A. Thayer M.R. Dougherty B.L. Grumm R.L. Milliken B.D. Radocinski R.G. Wiedenbeck M.E. Christian E.R. Shuman S. Trexel H. von Rosenvinge T.T. Binns W.R. Crary D.J. Dowkontt P. Epstein J. Hink P.L. Klarmann J. Lijowski M. Olevitch M.A. 《Space Science Reviews》1998,86(1-4):285-356
The Cosmic-Ray Isotope Spectrometer is designed to cover the highest decade of the Advanced Composition Explorer's energy
interval, from ∼50 to ∼500 MeV nucl−1, with isotopic resolution for elements from Z≃2 to Z≃30. The nuclei detected in this
energy interval are predominantly cosmic rays originating in our Galaxy. This sample of galactic matter can be used to investigate
the nucleosynthesis of the parent material, as well as fractionation, acceleration, and transport processes that these particles
undergo in the Galaxy and in the interplanetary medium.
Charge and mass identification with CRIS is based on multiple measurements of dE/dx and total energy in stacks of silicon
detectors, and trajectory measurements in a scintillating optical fiber trajectory (SOFT) hodoscope. The instrument has a
geometrical factor of ∼r250 cm2 sr for isotope measurements, and should accumulate ∼5×106 stopping heavy nuclei (Z>2) in two
years of data collection under solar minimum conditions.
This revised version was published online in June 2006 with corrections to the Cover Date. 相似文献
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基于预估校正和嵌套网格的虚拟飞行数值模拟 总被引:1,自引:0,他引:1
针对导弹虚拟飞行数值模拟问题,发展了空气动力学/飞行力学数值计算方法和软件。控制方程为非定常雷诺时均Navier-Stoker(RANS)方程和刚体六自由度运动方程;流场求解器为有限体积法结构网格求解器,时间推进采用双时间步法,湍流模型为Spalart-Allmaras一方程模型;采用Adams预估校正法实现飞行力学方程与流场控制方程的耦合计算;使用嵌套网格方法模拟多体运动。首先模拟了美国国家航空航天局(NASA)窄条翼导弹模型纵向虚拟飞行,研究耦合方式和时间步长的影响。仿真结果表明,双时间步三阶Adams耦合方法,同等精度下可以显著增大时间步长,缩短仿真时间。最后,采用该方法模拟了导弹自由摇滚特性和纵向虚拟飞行,模拟结果与试验值吻合较好。 相似文献
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分布式边界层吸入推进系统的建模与分析 总被引:2,自引:0,他引:2
机体后部边界层吸入技术可显著改善飞机的燃油经济性,但目前尚未建立推进系统设计与分析方法。针对类似N3-X飞机的分布式边界层吸入推进系统,采用基于边界层积分方程的数值分析方法,引入功推比参数,详细分析边界层状态和推进系统参数对系统性能的影响,从而为推进系统设计提供理论和数据支撑。通过基准状态与N3-X的对比,验证了计算方法的可靠性。分析表明,当吸入边界层占比为50%左右时推进系统能耗可降低4%,边界层形状因子越小或者动量厚度越大,能耗降低越多;进气道扩张比对功推比的影响不大;随着进气道入口马赫数增大、风扇压比降低、风扇效率增大、风扇损失降低或者喷流速度降低,功推比都会下降。 相似文献