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91.
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把Rodrigue和Wolitzer(1995)提出的一种新型显格式应用于热传导方程有限差分区域分裂算法的内边界点,并得到这类显—隐算法的收效性结果。新算法的逼近阶较好,而且较纯新型显式方法可以节省一倍左右的计算量。 相似文献
93.
并行扫描转换算法,采用通过多边形顶点的扫描线对扫描转换区间进行划分,使划分在各个区域的子多边形都是梯形,这既在一定区域内保持了各种相关性,又消除了对奇点的处理,同时对梯形的扫描转换不需要求交计算而只进行增量计算,提高了扫描转换速度。 相似文献
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P.A. Curran R.L.C. Starling A.J. van der Horst R.A.M.J. Wijers M. de Pasquale M. Page 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
The complex structure of the light curves of Swift GRBs (e.g. superimposed flares and shallow decay) has made their interpretation and that of the blast wave caused by the burst, more difficult than in the pre-Swift era. We aim to constrain the blast wave parameters: electron energy distribution, p, density profile of the circumburst medium, k, and the continued energy injection index, q. We do so by comparing the observed multi-wavelength light curves and X-ray spectra of a Swift sample to the predictions of the blast wave model. 相似文献
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《中国航空学报》2016,(6):1527-1540
A generic aircraft usually loses its static directional stability at moderate angle of attack (typically 20–30?). In this research, wind tunnel studies were performed using an aircraft model with moderate swept wing and a conventional vertical tail. The purpose of this study was to investigate flow mechanisms responsible for static directional stability. Measurements of force, surface pressure and spatial flow field were carried out for angles of attack from 0? to 46? and sideslip angles from ?8? to 8?. Results of the wind tunnel experiments show that the vertical tail is the main contributor to static directional stability, while the fuselage is the main contributor to static directional instabil-ity of the model. In the sideslip attitude for moderate angles of attack, the fuselage vortex and the wing vortex merged together and changed asymmetrically as angle of attack increased on the wind-ward side and leeward side of the vertical tail. The separated asymmetrical vortex flow around the vertical tail is the main reason for reduction in the static directional stability. Compared with the wing vortices, the fuselage vortices are more concentrated and closer to the vertical tail, so the yaw-ing moment of vertical tail is more unstable than that when the wings are absent. On the other hand, the attached asymmetrical flow over the fuselage in sideslip leads to the static directional instability of the fuselage being exacerbated. It is mainly due to the predominant model contour blockage effect on the windward side flow over the model in sideslip, which is strongly affected by angle of attack. 相似文献
99.
本文提出了用转化机构法进行单自由度复杂平面连杆机构的运动分析.基本思想是通过改变机构的原动件或机架或同时改变原动件和机架,以简化机构的运动分析.这种方法对常见的平面复杂连杆机构的运动分析非常有效,无需进行复杂的试凑或迭代.同时本文提出的这种解法有较为广泛的意义,对加深认识机构的组成以及对机构其它问题的研究都是+分重要的. 相似文献
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B.C. Joshi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2006,38(12):2725-2727
The double pulsar system, J0737–3039, provides a unique probe of a pulsar magnetosphere due to its edge-on viewing geometry, a tight orbit and a significant rate of advance of the angle of periastron. In this paper, we report on the changes in radio emission from the long period pulsar in this system, J0737–3039B, over a period of 9 months. Observations of this system with Giant Metrewave Radio Telescope (GMRT) show that the duration of the first bright phase of the pulsar centered at 210° orbital longitude from the ascending node is shrinking. These observations will be useful to constrain the proposed models for this system. 相似文献