全文获取类型
收费全文 | 145篇 |
免费 | 117篇 |
国内免费 | 47篇 |
专业分类
航空 | 205篇 |
航天技术 | 52篇 |
综合类 | 8篇 |
航天 | 44篇 |
出版年
2023年 | 9篇 |
2022年 | 23篇 |
2021年 | 21篇 |
2020年 | 23篇 |
2019年 | 16篇 |
2018年 | 9篇 |
2017年 | 9篇 |
2016年 | 9篇 |
2015年 | 3篇 |
2014年 | 13篇 |
2013年 | 16篇 |
2012年 | 9篇 |
2011年 | 9篇 |
2010年 | 12篇 |
2009年 | 12篇 |
2008年 | 14篇 |
2007年 | 10篇 |
2006年 | 6篇 |
2005年 | 5篇 |
2004年 | 9篇 |
2003年 | 6篇 |
2002年 | 1篇 |
2001年 | 3篇 |
2000年 | 6篇 |
1999年 | 3篇 |
1998年 | 8篇 |
1997年 | 10篇 |
1996年 | 6篇 |
1995年 | 12篇 |
1994年 | 3篇 |
1993年 | 3篇 |
1992年 | 2篇 |
1991年 | 2篇 |
1990年 | 3篇 |
1989年 | 2篇 |
1988年 | 1篇 |
1987年 | 1篇 |
排序方式: 共有309条查询结果,搜索用时 359 毫秒
51.
Numerical investigation of the impact of asymmetric fuel injection on shock train characteristics 总被引:1,自引:0,他引:1
Numerical simulations are carried out to investigate the impact of asymmetric fuel injection on shock train characteristics using the commercial-code FLUENT. The asymmetry of fuel injection is examined by changing the fuel flow rates of the upper and lower wall fuel injectors. The numerical approach solves the two-dimensional Reynolds-averaged Navier–Stokes (RANS) equations, supplemented with a k-ω model of turbulence. As a result, different ways of fuel injections will always lead to shock train transitions, with the variations of shock train structure, strength and leading edge position. For symmetric fuel injection, the flowfield of the isolator is quite asymmetric with the boundary layer of the upper wall side developing much stronger than that of the lower wall, which is due to the heterogeneity of the incoming flow. Regarding to asymmetric fuel injection with more of lower wall side, though the pressures in the combustor are nearly the same, the first shock of the shock train converts between ‘Distinct symmetric X type shock’ and ‘Obscure and weaker asymmetric shock’ and the shock train leading edge moves upstream with the increase of the asymmetry level. With regard to asymmetric fuel injection with more of upper wall side, ‘incomplete asymmetric X type shock’ occurs and the shock train structures keep nearly the same with low level of fuel injection asymmetry. Unexpected results like unstart will happen when increasing the level of fuel injection asymmetry. And the isolator will come back to normal state by decreasing the differential of upper and lower wall sides fuel injections. 相似文献
52.
53.
54.
55.
56.
内并联式TBCC进气道模态转换过程流动特性分析 总被引:4,自引:0,他引:4
针对组合动力(TBCC)进气道模态转换过程中出现的非定常气动现象,采用稳态/非稳态数值模拟方法对相关流动特性及其影响因素与流动机理开展了研究。结果表明:由涡轮发动机工作状态向冲压发动机工作模态转换过程中,进气道内出现结尾激波沿流向前后振荡现象,振荡频率约为130Hz;当冲压流道反压引起的激波未前传至模态转换分流板前时,冲压发动机工作状态对结尾激波振荡不产生影响。在相同的发动机工作状态下,随着模态转换速度的增加,结尾激波振荡频率逐渐增大。文中研究的进气道内结尾激波振荡现象可通过亚声速管道内波的传播理论进行解释和分析。 相似文献
57.
N. Gopalswamy H. Xie P. Mäkelä S. Yashiro S. Akiyama W. Uddin A.K. Srivastava N.C. Joshi R. Chandra P.K. Manoharan K. Mahalakshmi V.C. Dwivedi R. Jain A.K. Awasthi N.V. Nitta M.J. Aschwanden D.P. Choudhary 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Employing coronagraphic and EUV observations close to the solar surface made by the Solar Terrestrial Relations Observatory (STEREO) mission, we determined the heliocentric distance of coronal mass ejections (CMEs) at the starting time of associated metric type II bursts. We used the wave diameter and leading edge methods and measured the CME heights for a set of 32 metric type II bursts from solar cycle 24. We minimized the projection effects by making the measurements from a view that is roughly orthogonal to the direction of the ejection. We also chose image frames close to the onset times of the type II bursts, so no extrapolation was necessary. We found that the CMEs were located in the heliocentric distance range from 1.20 to 1.93 solar radii (Rs), with mean and median values of 1.43 and 1.38 Rs, respectively. We conclusively find that the shock formation can occur at heights substantially below 1.5 Rs. In a few cases, the CME height at type II onset was close to 2 Rs. In these cases, the starting frequency of the type II bursts was very low, in the range 25–40 MHz, which confirms that the shock can also form at larger heights. The starting frequencies of metric type II bursts have a weak correlation with the measured CME/shock heights and are consistent with the rapid decline of density with height in the inner corona. 相似文献
58.
59.
V.B. Baranov 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2009
An interface between the fully ionized hydrogen plasma of the solar wind (SW) and the partially ionized hydrogen gas flow of the local interstellar medium (LISM) is formed as a region where there is a strong interaction between these two flows. The interface is bounded by the solar wind termination shock (TS) and the LISM bow shock (BS) and is separated on two regions by the heliopause (HP) separating the solar wind and charged component of the LISM (plasma component below). The BS is formed due to the deceleration of the supersonic LISM flow relative to the solar system. Regions of the interface between the TS and HP and between the HP and BS were in literature named as the inner and outer heliosheaths, respectively. An investigation of the structure and physical properties of the heliosheath is at present especially interested due to the fact that Voyager-1 and Voyager-2 have crossed the TS in December 2004 (Burlaga, L.F., Ness, N.F., Acuna, M.Y., et al. Crossing the termination shock into the the heliosheath. Magnetic fields. Science 309, 2027–2029, 2005; Fisk, L.A. Journey into the unknown beyond. Science 309, 2016–2017, 2005; Decker, R.B., Krimigis, S.M., Roelof, E.C., et al. Voyager 1 in the foreshock, termination shock and heliosheath. Science 309, 2020–2024, 2005; Stone, E.C., Cummings, A.C., McDonald, F.B., et al. Voyager 1 explores the termination shock region and the heliosheath beyond. Science 309, 2017–2020, 2005) and in September 2007 (Jokipii, J.R. A shock for Voyager 2. Nature 454, 38–39, 2008; Gurnett, D.A., Kurth, W.S. Intense plasma waves at and near the solar wind termination shock. Nature 454, 78–80, 2008. doi: 10.1038/nature07023; Wang, L., Lin, R.P., Larson, D.E., Luhmann, J.G. Domination of heliosheath pressure by shock-accelerated pickup ions from observations of neutral atoms. Nature 454, 81–83, 2008. doi: 10.1038/nature07068.14; Burlaga, L.F., Ness, N.F., Acuna, M.H., et al. Magnetic fields at the solar wind termination shock. Nature 454, 75–77, 2008. doi: 10.1038/nature07029; Richardson, J.D., Kasper, J.C., Wang, C., et al. Cool heliosheath plasma and deceleration of the upstream solar wind at the termination shock. Nature 454, 63–66, 2008. doi: 10.1038/nature07024; Stone, E.C., Cummings, A.C., McDonald, F.B., et al. An asymmetric solar wind termination shock. Nature 454, 71–74, 2008. doi: 10.1038/nature07022; Decker, R.B., Krimigis, S.M., Roelof, E.C., et al. Mediation of the solar wind termination shock by non-thermal ions. Nature 454, 67–70, 2008. doi: 10.1038/nature 07030), respectively, and entered to the inner heliosheath. 相似文献
60.
采用伪速度冲击响应谱(PVSRS)对航天器蜂窝夹层结构进行了冲击破坏边界评估。目前航天领域常用的冲击响应谱(SRS)是绝对加速度谱(AASRS),相较于绝对加速度谱,伪速度谱能更清楚地显示出结构在低频、中频和高频段不同的冲击响应特征。分析了弹性力和惯性力在低频、中频和高频段对结构安全性的影响,据此在对数四坐标伪速度谱上给出了相应的结构破坏边界。以一典型蜂窝夹层结构为研究对象,通过有限元分析计算得到的结构破坏边界与伪速度谱给出的结构破坏边界符合得较好。在航天器结构冲击安全性研究领域,本文采用的伪速度谱结构冲击破坏边界是对目前常用的加速度谱方法的一个有益补充。 相似文献