全文获取类型
收费全文 | 1408篇 |
免费 | 221篇 |
国内免费 | 340篇 |
专业分类
航空 | 1116篇 |
航天技术 | 312篇 |
综合类 | 230篇 |
航天 | 311篇 |
出版年
2024年 | 3篇 |
2023年 | 20篇 |
2022年 | 40篇 |
2021年 | 58篇 |
2020年 | 58篇 |
2019年 | 63篇 |
2018年 | 64篇 |
2017年 | 56篇 |
2016年 | 73篇 |
2015年 | 75篇 |
2014年 | 99篇 |
2013年 | 61篇 |
2012年 | 96篇 |
2011年 | 115篇 |
2010年 | 85篇 |
2009年 | 87篇 |
2008年 | 76篇 |
2007年 | 94篇 |
2006年 | 91篇 |
2005年 | 58篇 |
2004年 | 59篇 |
2003年 | 42篇 |
2002年 | 55篇 |
2001年 | 48篇 |
2000年 | 35篇 |
1999年 | 36篇 |
1998年 | 43篇 |
1997年 | 35篇 |
1996年 | 38篇 |
1995年 | 26篇 |
1994年 | 41篇 |
1993年 | 17篇 |
1992年 | 29篇 |
1991年 | 34篇 |
1990年 | 21篇 |
1989年 | 23篇 |
1988年 | 8篇 |
1987年 | 4篇 |
1986年 | 2篇 |
1984年 | 1篇 |
排序方式: 共有1969条查询结果,搜索用时 312 毫秒
801.
钟华梁 《南京航空航天大学学报》1995,27(2):161-166
结合亚纯函数的亏值,讨论了当高阶导数具有一个分担值或分担函数时两个亚统函数的等价性,得出两点结论:(1)设f与g是两个亚约函数,满足δ(∞,f)=δ(∞,g)=1.若对某个n≥1有f(n)与g(n)分担值1,且,则f(n)·g(n)≡1或f-g≡k。(2)设f与g为整函数,满足,若对某个n≥1,f(n)与g(n)分担值1,δ(0,f)>0且0为g的Picard例外值,则f≡g或。 相似文献
802.
本文从无阻尼系统出发,理论上分析了转子系统振动方程的特征根,特征向量所具有的特点。除讨论正交性外,还进行了模态空间完备性的分析,推出转子系统强迫振动响应的解析表达式和传递函数的表达式,为参数辨识提供了理论依据。 相似文献
803.
谱载下基于模糊Miner法则的疲劳寿命估算 总被引:7,自引:0,他引:7
在载荷谱中,当疲劳应力稍低于疲劳极限时,对构件是否造成损伤呈现出某种"模糊"过渡状态.运用模糊数学的隶属函数,建立了考虑"模糊"损伤状态的Miner法则.按照常规Miner法则和模糊Miner法则,分别给出了程序块谱作用下疲劳寿命的估算公式.实例估算与试验结果的对比表明:采用模糊Miner法则,可使疲劳寿命的估算误差减少18.33%. 相似文献
804.
直线度误差目标函数凸凹性的研究 总被引:1,自引:1,他引:1
证明了直线度误差最小区域评定法的目标函数是一维欧式空间R1中的连续、不可微的凸函数 ,从而证明了目标函数的全局极小值是唯一的。 相似文献
805.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(7):1831-1842
The present paper has investigated the associations of solar activity (SA), represented by total solar irradiance (TSI), galactic cosmic rays (GCR) and terrestrial climate parameters in particular the global cloudiness and global surface temperature. To that end, we have analysed thirty five years (1983–2018) data of these parameters and have applied the Granger-causality test in order to assess whether there is any potential predictability power of one indicator to the other. The correlations among the involved parameters are tested using Vector Auto Regression (VAR) model and variance decomposition method. As a result of the above analysis, we have found that the TSI is an important factor and has contributed about 8.77 ± 0.42% in the cosmic ray intensity variations. In case of cloud cover variations, the other three parameters (TSI, cosmic ray and global surface temperature) have played a significant role. Further, the TSI changes have contributed 1.68 ± 0.03% fluctuations in the variance of the cloud cover while the cosmic ray intensity and global surface temperature have contributed about 4.89 ± 0.08% and 10.87 ± 1.41% respectively. In case of the global surface temperature anomaly both TSI and cloud covers have contributed about 5.07 ± 0.47% and 14.42 ± 2.13% fluctuations respectively. Additionally, we have also assessed the impact of internal climate oscillations like multivariate ENSO index (MEI), north Atlantic oscillations (NAO) and quasi biennial oscillations (QBO) on cloud cover variations. The contribution of these internal oscillations e.g. ENSO, NAO and QBO in cloud cover variation were reported as 7.48 ± 1.02%, 5.51 ± 0.16% and 1.36 ± 0.43% respectively. 相似文献
806.
《中国航空学报》2020,33(8):2204-2211
The stripped solar sail whose membrane is divided into separate narrow membrane strips is believed to have the best structural efficiency. In this paper, the stripped solar sail structure is regarded as an assembly made by connecting a number of boom-strip components in sequence. Considering the coupling effects between booms and membrane strips, an exact and semi-analytical method to calculate structural dynamic responses of the stripped solar sail subjected to solar radiation pressure is established. The case study of a 100 m stripped solar sail shows that the stripped architecture helps to reduce the static deflections and amplitudes of the steady-state dynamic response. Larger prestress of the membrane strips will decrease stiffness of the sail and increase amplitudes of the steady-state dynamic response. Increasing thickness of the boom will benefit to stability of the sail and reduce the resonant amplitudes. This proposed semi-analytical method provides an efficient analysis tool for structure design and attitude control of the stripped solar sail. 相似文献
807.
《中国航空学报》2021,34(5):341-349
Aviation products would go through a multi-phase improvement in reliability performance during the research and development process. In the literature, most of the existing reliability growth models assume a constant failure intensity in each test phase, which inevitably limits the scope of the application. To address this problem, we propose two new models considering time-varying failure intensity in each stage. The proposed models borrow the idea from the accelerated failure-time models. It is assumed that time between failures follow the log-location-scale distribution and the scale parameters in each phase do not change, which forms the basis for integrating the data from all test stages. For the test-find-test scenario, an improvement factor is introduced to construct the relationship between two successive location parameters. Whereas for the test-fix-test scenario, the instantaneous cumulative time between failures is assumed to be consistent with Duane model and derive the formulation of location parameter. Likelihood ratio test is further utilized to test whether the assumption of constant failure intensity in each phase is suitable. Several applications with real reliability growth data show that the assumptions are reasonable and the proposed models outperform the existing models. 相似文献
808.
A unifying approach in simulating the shot peening process using a 3D random representative volume finite element model 总被引:1,自引:0,他引:1
Using a modified 3D random representative volume (RV) finite element model,the effects of model dimensions (impact region and interval between impact and representative regions),model shapes (rectangular,square,and circular),and peening-induced thermal softening on resultant critical quantities (residual stress,Almen intensity,coverage,and arc height) after shot peening are systematically examined.A new quantity,i.e.,the interval between impact and representative regions,is introduced and its optimal value is first determined to eliminate any boundary effect on shot peening results.Then,model dimensions are respectively assessed for all model shapes to reflect the actual shot peening process,based on which shape-independent critical shot peening quantities are obtained.Further,it is found that thermal softening of the target material due to shot peening leads to variances of the surface residual stress and arc height,demonstrating the necessity of considering the thermal effect in a constitutive material model of shot peeing.Our study clarifies some of the finite element modeling aspects and lays the ground for accurate modeling of the SP process. 相似文献
809.
Man-Lian Zhang Libo Liu Weixing Wan Baiqi Ning 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
In this paper, we present our recent work on developing an updated global model of the ionospheric F2 peak height hmF2 parameter by combining data from the Constellation Observing System for Meteorology, Ionosphere and Climate (COSMIC/FORMOSAT-3) radio occultation (RO) measurements and from the extended global ionosonde stations. In particular, 10 Chinese ionosonde stations’ data are newly introduced into this study. The modeling technique used is based on a two-layer empirical orthogonal function (EOF) expansion. Global distributions of hmF2 maps calculated using the newly constructed global model and the one provided by the International Reference Ionosphere model (IRI-ITU-R) are compared with the global distributions of hmF2 obtained by the COSMIC RO measurements and quantitative statistical analysis of the differences between the model results and those of the COSMIC RO measurements is made for the low (2008) and high (2012) solar activity years. The obtained average root-mean-square differences (RMSEs) for our model are 27.7 km (11.1%) and 31.0 km (9.8%), respectively for the years 2008 and 2012, whereas those for the IRI-ITU-R model are 39.9 km (16.9%) and 35.0 km (11.6%), respectively. Comparison of the results calculated both by our model and the IRI-ITU-R model with the digisonde observation is also made. The comparisons show that the newly constructed global hmF2 model can reproduce reasonably well the observations and perform better than IRI-ITU-R model. 相似文献
810.
提出了一种结合图像中值滤波和试件参考点的风洞压敏涂料(PSP)试验图像数据处理方法。与通常用校准箱获取校准曲线进而得到PSP试验试件表面压力或压力系数(Cp)的方法不同,该方法通过空心中值滤波技术恢复PSP光强比图像中测压孔处的光强比数据,结合若干参考点处常规测压技术实测所得Cp值,获得Cp值和PSP图像光强比数据的关系曲线,进而得到整个试件表面的Cp值数据,该方法获得的数据结合了风洞试验诸多因素对试验结果的影响。利用MATLAB对PSP技术试验图像数据进行了处理,并将PSP方法获得的Cp值与常规测压方法获得的Cp值进行了比较,得到的结果显示,笔者采用的方法获得的Cp值与常规测压方法获得的Cp值吻合较好。该方法为PSP图像数据的处理提供了一种新的方法,具有较大的发展潜力和应用价值。 相似文献