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51.
整体加筋壁板的破损安全特性与断裂控制分析 总被引:2,自引:2,他引:2
用有限元和断裂力学方法分析大型整体机翼下壁板的破损安全特性。对一个九桁条铝合金整体加筋板,裂纹从断裂筋条下向两侧均匀扩展的开裂形式,进行了应力强度因子和剩余强度计算,并和另一个具有相同构形的铆接加筋板的结果进行对比。当裂纹长度在两倍桁条间距以内时两种加筋板的剩余强度水平相当。但是当整体壁板中的裂纹穿过外侧相邻桁条时,整体桁条的止裂能力逐渐减弱。研究对整体壁板蒙皮胶接止裂条的断裂控制措施及有限元建模分析方法,描述止裂条胶层局部脱粘的处理方法和迭代过程。止裂条材料分别选用了钛合金和单向层压复合材料。计算结果说明胶接止裂措施能显著提高整体加筋板的破损安全性能。 相似文献
52.
C. Fröhlich 《Space Science Reviews》2006,125(1-4):53-65
Since November 1978 a set of total solar irradiance (TSI) measurements from space is available, yielding a time series of
more than 25 years. Presently, there are three TSI composites available, called PMOD, ACRIM and IRMB, which are all constructed
from the same original data, but use different procedures to correct for sensitivity changes. The PMOD composite is the only
one which also corrects the early HF data for degradation. The results from the detailed analysis of the VIRGO radiometry
allow a good understanding of the effects influencing the long-term behaviour of classical radiometers in space. Thus, a re-analysis
of the behaviour of HF/NIMBUS-7 and ACRIM-I/SMM was indicated. For the former the situation is complicated by the fact that
there are no in-flight means to determine changes due to exposure to solar radiation by comparison with a less exposed radiometer
on the same spacecraft. The geometry and optical property of the cavity of HF is, however, very similar to the PMO6-type radiometers,
so the behaviour of the PMO6V radiometers on VIRGO can be used as a model. ACRIM-I had to be revised mainly due to a henceforth
undetected early increase and a more detailed analysis of its degradation. The results are not only important for solar radiometry
from space, but they also provide a more reliable TSI during cycle 21. The differences between the revised PMOD composite
and the ACRIM and IRMB are discussed by comparison with a TSI reconstruction from Kitt-Peak magnetograms. As the PMOD composite
is the only one which has reliable data for cycle 21, the behaviour of the three solar cycles can now be compared and the
similarities and differences discussed. 相似文献
53.
Y. Futaana S. Barabash A. Grigoriev D. Winningham R. Frahm M. Yamauchi R. Lundin 《Space Science Reviews》2006,126(1-4):315-332
As a part of the global plasma environment study of Mars and its response to the solar wind, we have analyzed a peculiar case
of the subsolar energetic neutral atom (ENA) jet observed on June 7, 2004 by the Neutral Particle Detector (NPD) on board
the Mars Express satellite. The “subsolar ENA jet” is generated by the interaction between the solar wind and the Martian
exosphere, and is one of the most intense sources of ENA flux observed in the vicinity of Mars. On June 7, 2004 (orbit 485
of Mars Express), the NPD observed a very intense subsolar ENA jet, which then abruptly decreased within ∼10 sec followed
by quasi-periodic (∼1 min) flux variations. Simultaneously, the plasma sensors detected a solar wind structure, which was
most likely an interplanetary shock surface. The abrupt decrease of the ENA flux and the quasi-periodic flux variations can
be understood in the framework of the global response of the Martian plasma obstacle to the interplanetary shock. The generation
region of the subsolar ENA jet was pushed towards the planet by the interplanetary shock; and therefore, Mars Express went
out of the ENA jet region. Associated global vibrations of the Martian plasma obstacle may have been the cause of the quasi-periodic
flux variations of the ENA flux at the spacecraft location. 相似文献
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56.
R. C. Wiens D. S. Burnett C. M. Hohenberg A. Meshik V. Heber A. Grimberg R. Wieler D. B. Reisenfeld 《Space Science Reviews》2007,130(1-4):161-171
The Genesis mission returned samples of solar wind to Earth in September 2004 for ground-based analyses of solar-wind composition,
particularly for isotope ratios. Substrates, consisting mostly of high-purity semiconductor materials, were exposed to the
solar wind at L1 from December 2001 to April 2004. In addition to a bulk sample of the solar wind, separate samples of coronal
hole (CH), interstream (IS), and coronal mass ejection material were obtained. Although many substrates were broken upon landing
due to the failure to deploy the parachute, a number of results have been obtained, and most of the primary science objectives
will likely be met. These objectives include He, Ne, Ar, Kr, and Xe isotope ratios in the bulk solar wind and in different
solar-wind regimes, and 15N/14N and 18O/17O/16O to high precision. The greatest successes to date have been with the noble gases. Light noble gases from bulk solar wind
and separate solar-wind regime samples have now been analyzed. Helium results show clear evidence of isotopic fractionation
between CH and IS samples, consistent with simplistic Coulomb drag theory predictions of fractionation between the photosphere
and different solar-wind regimes, though fractionation by wave heating is also a possible explanation. Neon results from closed
system stepped etching of bulk metallic glass have revealed the nature of isotopic fractionation as a function of depth, which
in lunar samples have for years deceptively suggested the presence of an additional, energetic component in solar wind trapped
in lunar grains and meteorites. Isotope ratios of the heavy noble gases, nitrogen, and oxygen are in the process of being
measured. 相似文献
57.
58.
为解决太阳能无人机(UAV)总体设计中任务需求表达模糊、技术指标重要度排序决策困难的问题,提出了基于模糊质量功能展开(FQFD)的太阳能无人机总体设计指标排序方法。该方法在传统质量功能展开(QFD)质量屋的基础上,引入三角模糊数,表征任务需求的不确定性和模糊性;在模糊隶属度函数未知的情况下,采用α加权修正水平截集去模糊化方法计算技术指标重要度,获得技术指标重要度排序,为总体设计优化决策提供依据。最后以长航时太阳能无人机的总体设计为例,对任务需求—工程特性—技术指标的两级质量屋模型进行计算分析,得到续航能力、巡航高度、动力系统效率、巡航速度和气动效率是太阳能无人机最重要的5个技术指标的结果。此方法客观性较强,可处理复杂的系统不确定性,为太阳能无人机总体方案设计及决策应用提供参考依据。 相似文献
59.
为了能够在设计阶段早期对复合材料加筋壁板制造成本进行快速估算,提出了一种以结构设计重量为主要驱动因素的制造成本估算模型。该模型的关键是考虑了诸如材料成本比重系数、制造工艺系数、蒙皮形状系数、筋条形状系数、材料利用率系数等合理取值。以某验证试验的试验件制造成本估算为例,估算成本与实际制造成本的偏差为10.8%,说明了采用该方法对复合材料加筋壁板制造成本进行快速估算的结果是可以为设计人员提供决策依据的。 相似文献
60.