全文获取类型
收费全文 | 2143篇 |
免费 | 341篇 |
国内免费 | 332篇 |
专业分类
航空 | 1306篇 |
航天技术 | 702篇 |
综合类 | 352篇 |
航天 | 456篇 |
出版年
2024年 | 9篇 |
2023年 | 33篇 |
2022年 | 54篇 |
2021年 | 55篇 |
2020年 | 78篇 |
2019年 | 81篇 |
2018年 | 80篇 |
2017年 | 76篇 |
2016年 | 102篇 |
2015年 | 100篇 |
2014年 | 111篇 |
2013年 | 115篇 |
2012年 | 153篇 |
2011年 | 153篇 |
2010年 | 129篇 |
2009年 | 113篇 |
2008年 | 83篇 |
2007年 | 111篇 |
2006年 | 113篇 |
2005年 | 70篇 |
2004年 | 74篇 |
2003年 | 104篇 |
2002年 | 84篇 |
2001年 | 64篇 |
2000年 | 77篇 |
1999年 | 58篇 |
1998年 | 72篇 |
1997年 | 42篇 |
1996年 | 66篇 |
1995年 | 56篇 |
1994年 | 58篇 |
1993年 | 50篇 |
1992年 | 47篇 |
1991年 | 35篇 |
1990年 | 49篇 |
1989年 | 33篇 |
1988年 | 20篇 |
1987年 | 6篇 |
1986年 | 2篇 |
排序方式: 共有2816条查询结果,搜索用时 546 毫秒
731.
根据火箭控制系统闭环模飞的方案, 讨论了平台系统中惯性器件激励电流的计算方法, 其中考虑了地球自转对陀螺的影响。根据工程需要对公式进行了简化 相似文献
732.
733.
734.
735.
736.
737.
Multilevel Tests and Measurement Evaluation Methods for the Application of Composite Materials in Spacecraft Structures
下载免费PDF全文
![点击此处可从《上海航天》网站下载免费的PDF全文](/ch/ext_images/free.gif)
LIU Bo WANG Jinming HAN Han TAO Jingy LIU Tao ZHANG Xiaodong YI Guo LIU Yihui 《上海航天》2022,39(1):111-121
With the implementation of new-generation launch vehicles, space stations, lunar and deep space exploration, etc., the development of spacecraft structures will face new challenges. In order to reduce the spacecraft weight and increase the payload, composite material structures will be widely used. It is difficult to evaluate the strength and life of composite materials due to their complex mechanism and various phenomena in damage and failure. Meanwhile, the structures of composite materials used in spacecrafts will bear complex loads, including the coupling loads of tension, pressure, bending, shear, and torsion. Static loads, thermal loads, and vibration loads may occur at the same time, which asks for verification requirements to ensure the structure safety. Therefore, it is necessary to carry out a systematic multi-level experimental study. In this paper, the building block approach (BBA) is used to investigate the multilevel composite material structures for spacecrafts. The advanced measurement technology is adopted based on digital image correlation (DIC) and piezoelectric and optical fiber sensors to measure the composite material structure deformation. The virtual experiment technology is applied to provide sufficient and reliable data for the evaluation of the composite material structures of spacecrafts. 相似文献
738.
739.
YANG Zhi-min 《航空动力学报》2014,29(5):1014-1019
The apparatus of scan measurement was used to gather the temperature pattern at the combustor outlet,where the average working temperature of gas was about 1700Kand the maximum temperature was about 1 950K.Consequently,the measurement part was cooled by water or air.Usually,for intermittent measurement devices,the interval of circle angel could be changed to get a high-density temperature distribution.A continuous measurement manner was adopted to get point in circle.The angle between two measurepoints was 1.286°.The annular combustor outlet was about 40to 50mm in height,where 5or 6measure points were usually arranged.In this device,10measure points were arranged in a range of 45.5mm.Four thermocouples were arranged in circle to obtain 2 800measure-points of the temperature field in a single experiment.Data were drawn from the whole datasheet at intervals.Each group of data whose number decreased in turn,included temperature points of 2 800,1 400,700,and 350,respectively.Several groups of temperature distributions with different densities were established.Subsequently,data processing was conducted to calculate the main combustor characteristics,including arithmetic or integral average temperature,OTDF(overall temperature distribution factor)and RTDF(radial temperature distribution factor).It is found that the data from different groups with different measuring densities result in significant difference on the combustor characteristics.The veracity of temperature characteristics increases with the growing measure-density. 相似文献
740.
在航空发动机和燃气轮机燃烧室部件试验中,取样密度会对燃烧室出口温度测量结果产生影响,如果取样密度过小,会造成燃烧室出口温度测量值与"实际值"之间偏离度过大。基于此,对3种燃烧室的试验数据进行了分析。同时将试验采集到的"高取样密度"的原始数据沿圆周方向进行均匀"拆分","拆分后"得到不同密度的"低取样密度"数据,将该数据与原始"高取样密度"试验数据的分析结果进行了对比,得出了取样密度与测量偏离度之间的关系,并给出了满足工程研制需要的取样密度。 相似文献