全文获取类型
收费全文 | 81篇 |
免费 | 37篇 |
国内免费 | 32篇 |
专业分类
航空 | 104篇 |
航天技术 | 19篇 |
综合类 | 10篇 |
航天 | 17篇 |
出版年
2023年 | 4篇 |
2022年 | 11篇 |
2021年 | 9篇 |
2020年 | 8篇 |
2019年 | 4篇 |
2018年 | 6篇 |
2017年 | 3篇 |
2016年 | 5篇 |
2015年 | 3篇 |
2014年 | 11篇 |
2013年 | 16篇 |
2012年 | 6篇 |
2011年 | 8篇 |
2010年 | 4篇 |
2009年 | 5篇 |
2008年 | 5篇 |
2007年 | 1篇 |
2006年 | 2篇 |
2005年 | 2篇 |
2003年 | 1篇 |
2002年 | 4篇 |
2001年 | 4篇 |
2000年 | 4篇 |
1999年 | 4篇 |
1998年 | 1篇 |
1997年 | 1篇 |
1996年 | 2篇 |
1995年 | 2篇 |
1994年 | 3篇 |
1992年 | 3篇 |
1991年 | 3篇 |
1990年 | 4篇 |
1989年 | 1篇 |
排序方式: 共有150条查询结果,搜索用时 62 毫秒
41.
42.
Angela Gardini Monica Laurenza Marisa Storini 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
Fifteen solar energetic particle (SEP) events have been analyzed using proton flux data recorded by the Helios 1, Helios 2, and IMP 8 spacecraft in the energy range ∼4–40 MeV during 1974–1982. For each of the events at least two of the spacecraft have their nominal magnetic footpoint within 20° in heliocentric longitude from each other. The SEP events are sub-grouped as a function of their heliocentric longitudinal separation and heliocentric radial distance from the SEP associated solar flare and several case studies are presented in this paper. Main results concerning their usage in estimating the SEP radial dependence are given. Moreover, we investigate the behavior of the third not connected spacecraft in order to study the dependence of the proton flux as a function of flare location. It is found that the contribution of the longitudinal gradient in determining variations in the SEP proton flux is particularly relevant for spacecraft having their magnetic connection footpoint separated from the flare between 30° and 50°. 相似文献
43.
A deduced cutting force prediction model for circular end milling process is presented in this paper. Traditional researches on cutting force model usually focus on linear milling process which does not meet other cutting conditions, especially for circular milling process. This paper presents an improved cutting force model for circular end milling process based on the typical linear milling force model. The curvature effects of tool path on chip thickness as well as entry and exit angles are analyzed, and the cutting force model of linear milling process is then corrected to fit circular end milling processes. Instantaneous cutting forces during circular end milling process are predicted according to the proposed model. The deduced cutting force model can be used for both linear and circular end milling processes. Finally, circular end milling experiments with constant and variable radial depth were carried out to verify the availability of the proposed method. Experiment results show that measured results and simulated results corresponds well with each other. 相似文献
44.
几种摇臂与联动环连接结构对比分析 总被引:2,自引:0,他引:2
为了改善航空发动机整体性能和可靠性,以航空发动机从地面起动到巡航过程为研究对象,采用热-固耦合分析方法,对涡轮转子叶尖径向运行间隙(BTRRC,Blade-tip Radial Running Clearance)进行动态分析.在分析中考虑了材料属性的非线性和温度载荷、离心载荷的动态性,分别对涡轮的叶片、盘和机匣的变形进行计算和分析,得到了涡轮叶尖径向运行间隙的变化规律,以及BTRRC最小点(可选择t=180 s)和最小值(约0.18 mm),为进行进一步涡轮叶尖径向运行间隙的动态概率分析和动态优化设计奠定了基础. 相似文献
45.
46.
Carlos Roberto Braga Alisson Dal Lago Guillermo Stenborg 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
The white light coronagraphs onboard SOHO (LASCO-C2 and -C3) and most recently STEREO (SECCHI -COR1 and -COR2) have detected a myriad of coronal mass ejections (CME). They are a key component of space weather and under certain conditions they can become geo-effective, hence the importance of their kinematic characterization to help predict their effects. However, there is still a lot of debate on how to define the event boundaries for space weather purposes, which in turn makes it difficult to agree on their kinematic properties. That lack of agreement is reflected in both the manual and automated CME catalogs in existence. To contribute to a more objective definition and characterization of white-light coronagraph events, Goussies et al. (2010) introduced recently the concept of “texture of the event”. Based on that property, they developed a supervised segmentation algorithm to allow the automatic tracking of dynamic events observed in the coronagraphs field of view, which is called CORonal SEgmentation Technique (CORSET). In this work, we have enhanced the capabilities of the algorithm by adding several new functionalities, namely the automatic computation of different morphological and kinematic parameters. We tested its performance on 57 well-studied limb CME events observed with the LASCO coronagraphs between 1997 and 2001, and compared the parameters obtained with those from three existent CME lists: two of them obtained from an observer-based detection and tracking method (i.e., two manual catalogs), and the other one based on the automated detection and characterization of the CME events (i.e., a fully automated catalog). We found that 51 events could be tracked and quantified in agreement with the CME definition. In general terms, the position angle, and the radial and expansion speeds are in agreement with the manual catalogs used for comparison. On the other hand, some discrepancies between CORSET and the automated catalog were found, which can be explained by the different delimitation of the CME angular extent. 相似文献
47.
采用能够测量由接触表面微动所导致迟滞现象的实验装置,对带有涂层材料的不同接触方式的实验件进行了接触刚度和微动磨损测试.通过接触刚度测试,研究了激振力幅值、激振频率和接触正压力对接触刚度的影响;通过微动磨损分析,研究接触方式和载荷条件接触表面形态的改变,以及工作时间对接触刚度的影响.通过分析和总结实验结果,阐述了干摩擦阻尼结构微动磨损的防护措施,为提高航空发动机结构部件的可靠性提供一定的理论依据和技术支持. 相似文献
48.
基于临界面法的燕尾榫连接结构微动疲劳寿命预测 总被引:5,自引:3,他引:2
以航空发动机叶片/轮盘之间的燕尾榫连接结构为研究对象,分析了燕尾榫连接结构接触应力与应变的变化.根据多轴疲劳临界损伤平面原理,在燕尾榫连接结构的微动疲劳寿命预测研究中引入多轴临界平面法的疲劳损伤参数CCB (Chu-Conle-Bonnen),FS (Fatemi-Socie),MSSR (modified shear stress rang)和SWT (Smith-Watson-Topper).将预测寿命与试验寿命进行对比,结果表明:在预测微动疲劳寿命时,4个参数中寿命预测的最大误差为23%,可较好地预测低周微动疲劳寿命.其中基于临界平面法的SWT参数预测误差最小,为1.23%;4个参数均预测裂纹萌生位置在接触区末端,与试验结果一致.在预测裂纹萌生角度上,FS,MSSR,SWT参数预测结果与试验较一致,CCB参数预测结果与试验结果相差较大.说明基于临界平面法的寿命预测模型具有较好的预测能力. 相似文献
49.
基于RBF网络辨识的挠性卫星姿态自适应控制 总被引:2,自引:0,他引:2
为满足挠性卫星姿态控制的更高要求,提出了一种基于径向基函数(RBF)网络辨识的模糊自适应控制方法。根据卫星姿态动力学方程,将RBF辨识网络引入模糊神经网络的T-S模型,以辨识卫星,在线修改模糊神经控制器(FNC)参数,使卫星的姿态角度达到设定值。仿真结果表明:该法能有效克服卫星的不确定性,提高卫星姿态的控制精度。 相似文献
50.