全文获取类型
收费全文 | 403篇 |
免费 | 162篇 |
国内免费 | 30篇 |
专业分类
航空 | 219篇 |
航天技术 | 189篇 |
综合类 | 4篇 |
航天 | 183篇 |
出版年
2024年 | 4篇 |
2023年 | 11篇 |
2022年 | 34篇 |
2021年 | 31篇 |
2020年 | 39篇 |
2019年 | 19篇 |
2018年 | 20篇 |
2017年 | 26篇 |
2016年 | 18篇 |
2015年 | 17篇 |
2014年 | 19篇 |
2013年 | 15篇 |
2012年 | 27篇 |
2011年 | 45篇 |
2010年 | 32篇 |
2009年 | 28篇 |
2008年 | 24篇 |
2007年 | 22篇 |
2006年 | 17篇 |
2005年 | 23篇 |
2004年 | 18篇 |
2003年 | 16篇 |
2002年 | 8篇 |
2001年 | 8篇 |
2000年 | 7篇 |
1999年 | 8篇 |
1998年 | 12篇 |
1997年 | 6篇 |
1996年 | 7篇 |
1995年 | 7篇 |
1994年 | 2篇 |
1993年 | 7篇 |
1992年 | 5篇 |
1991年 | 5篇 |
1990年 | 3篇 |
1989年 | 2篇 |
1988年 | 1篇 |
1987年 | 1篇 |
1984年 | 1篇 |
排序方式: 共有595条查询结果,搜索用时 31 毫秒
441.
442.
一种微波及毫米波滤波器的精确设计方法 总被引:3,自引:0,他引:3
介绍了一种微波及毫米波滤波器精确设计方法:由滤波器的原型参数,导出滤波器的广义阻抗变换系数;采用模匹配法或耦合积分方程技术等数值算法精确计算各个耦合结的S参数,进而转换成广义阻抗变换系数;通过插值,获得满足原型要求的滤波器各个耦合结的结构尺寸以及谐振腔长度,将结构参数代入模匹配程序、HFSS或CST软件进行分析,分析结果与预期值一致。设计了26GHz矩形波导带通滤波器,模匹配法和HFSS以及CST软件的仿真结果、测试数据与设计要求一致,说明该种设计方法是有效的。 相似文献
443.
444.
445.
446.
448.
Eliana Vieira Clara Lázaro M. Joana Fernandes 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(5):1737-1753
Due to the presence of water vapour and cloud liquid water in the atmosphere, the wet component of the troposphere is responsible for a delay in the propagation of the altimeter signals, the Wet Path Delay (WPD). The high space–time variability of the water vapour distribution makes the modelling of WPD difficult, its effect still being one of the main error sources in satellite altimetry applications, e.g. in the estimation of Mean Sea Level (MSL). The understanding and the quantification of the WPD variability on various spatial and temporal scales are the main purposes of this study, in view to improve the MSL error budget. The dominant timescales of WPD variability and its correlation with Sea Level Anomaly (SLA) are examined. In these analyses, the atmospheric reanalysis ERA-Interim model from the European Centre for Medium-Range Weather Forecasts (ECMWF) is used to derive a global dataset of daily grids of WPD, spanning a 28-year period from January 1988 to December 2015. The Seasonal-Trend decomposition procedure based on Loess (STL) is used to extract precise WPD annual and interannual signals. Linear trends have been derived from the interannual time series and the contribution of each STL component was mapped globally, allowing the understanding of the WPD variability in spatial terms. The correlation between SLA and WPD is mapped and decomposed into seasons using monthly mean grids, for a period of 21-years, from January 1993 to December 2013.Aiming at inspecting the sensitivity of the results to the used data set, the WPD temporal analysis is extended to the data set provided by the Special Sensor Microwave Imager (SSM/I) and SSM/I Sounder (SSM/IS) Sensors. The WPD from SSM/I(S) is compared against those from the ERA-Interim and from the National Centers for Environmental Prediction (NCEP).Results show that climate phenomena, especially the El Niño Southern Oscillation (ENSO) are the cause for this high variability, since they affect the water vapour and temperature. The observed trends from ERA-Interim, computed globally and over ocean regions only, allow concluding that WPD is increasing with time by approximately 0.1?mm per year, and the maximum trends are observed for the Pacific North and Indian Oceans. High correlation between WPD and SLA is found over the western tropical Pacific.The comparison between WPD from SSM/I(S) and from ERA-Interim and NCEP, allows concluding that the trends computed using only the SSM/I(S) measurement points are substantially larger. 相似文献
449.
以卫星单元肼推进系统轨控过程为研究对象,利用数值模拟手段研究了轨控过程中推进系统贮箱压力、贮箱温度、轨控时长等参数对轨控效果的定量影响,考察了在轨标定推力系数对于轨控模型的修正效果。选取某近地卫星对其轨道控制历史数据进行分析,通过在轨实测数据对轨控模型进行了验证。结果表明,采用在轨标定推力修正系数能够有效地降低轨道控制模型的平均误差,平均误差值从3.615%减至1.924%;通过参数敏感性分析,得出贮箱温度的总体影响不超过0.2%,贮箱压力的总体影响不超过5%。通过对点火时长的影响分析发现,在不同的贮箱压力下,存在一个特定的临界点火时长;轨控时长低于临界点火时长时,贮箱压力的变化将不会被压力传感器识别。针对某低轨卫星,寿命初期箱压1.8MPa时,临界点火时长为8.5秒;寿命末期0.5Mpa时,临界点火时长为319.8秒。 相似文献
450.
《中国航空学报》2020,33(12):2999-3010
Technological miniaturization has enabled the development of small satellites weighing as little as 1 kg. Unfortunately, there is still a lack of suitable efficient micropropulsion systems at these scales. The pulsed plasma thruster is a structurally simple form of electric propulsion. This simplicity also makes it ideally suited for miniaturization. Its history can be traced back to applications in satellites that are much larger than micro/nano-satellites. The vast majority of modern pulsed plasma thrusters use solid polytetrafluoroethylene (PTFE) as a propellant. Unfortunately, at lower discharge energy levels such as those necessitated by the power limitations of micro/nano-satellites, PTFE has a tendency to exhibit carbon deposition, which can ultimately lead to thruster failure. In this new era of small satellites, it is important to consider alternative propellants in the miniaturization of pulsed plasma thrusters. This brief review discusses the needs and limitations of small satellites and alternative propellants that may be able to meet these needs. Such propellants may be able to offer advantages such as a longer thruster lifetime, a higher specific impulse, or a higher thrust-to-power ratio. This would enable the development of different types of pulsed plasma thrusters that can be tailored towards specific mission requirements. 相似文献