全文获取类型
收费全文 | 10721篇 |
免费 | 1557篇 |
国内免费 | 2152篇 |
专业分类
航空 | 6198篇 |
航天技术 | 2923篇 |
综合类 | 2185篇 |
航天 | 3124篇 |
出版年
2024年 | 15篇 |
2023年 | 50篇 |
2022年 | 158篇 |
2021年 | 172篇 |
2020年 | 231篇 |
2019年 | 116篇 |
2018年 | 134篇 |
2017年 | 124篇 |
2016年 | 150篇 |
2015年 | 304篇 |
2014年 | 565篇 |
2013年 | 568篇 |
2012年 | 645篇 |
2011年 | 682篇 |
2010年 | 836篇 |
2009年 | 811篇 |
2008年 | 750篇 |
2007年 | 684篇 |
2006年 | 593篇 |
2005年 | 535篇 |
2004年 | 329篇 |
2003年 | 307篇 |
2002年 | 288篇 |
2001年 | 391篇 |
2000年 | 421篇 |
1999年 | 555篇 |
1998年 | 570篇 |
1997年 | 482篇 |
1996年 | 454篇 |
1995年 | 361篇 |
1994年 | 363篇 |
1993年 | 346篇 |
1992年 | 300篇 |
1991年 | 263篇 |
1990年 | 221篇 |
1989年 | 204篇 |
1988年 | 143篇 |
1987年 | 115篇 |
1986年 | 75篇 |
1985年 | 30篇 |
1984年 | 18篇 |
1983年 | 16篇 |
1982年 | 14篇 |
1981年 | 10篇 |
1980年 | 5篇 |
1974年 | 4篇 |
1973年 | 4篇 |
1967年 | 2篇 |
1965年 | 5篇 |
1900年 | 2篇 |
排序方式: 共有10000条查询结果,搜索用时 31 毫秒
621.
钛合金TB6铣削加工硬化实验 总被引:1,自引:0,他引:1
研究了使用涂层硬质合金刀具对钛合金TB6进行端铣加工时,铣削参数以及刀具后刀面磨损量对加工硬化(表面硬化率、硬化层深度以及硬化层硬度分布)的影响,以弄清TB6铣削硬化现象及机理.结果表明,在实验参数范围内,刀具无磨损的情况下,硬化率基本保持在107%~112%范围内,硬化层深度范围为18~36 μm;铣削速度增加时,加工硬化程度会有较为明显的降低现象,而进给量与切深对加工硬化的影响并不明显;刀具磨损对加工硬化的影响较为显著,后刀面磨损量低于0.2 mm时,硬化层深度随着磨损增加从30 μm增加至55 μm,而后刀面磨损量为0.35 mm时,硬化层深度达到了130 μm.刀具磨损后在加工表面下较浅位置出现软化区域,而且随着磨损量的增加,软化越来越明显. 相似文献
622.
623.
针对应用于飞行器增压系统的双级气体减压器,从单级气体减压器的有限体积瞬变仿真模型出发建立了其数值模型,并搭建了双级减压器特性研究系统的模块化仿真模型.通过大量的时域仿真研究了某两型具有细微设计差异的减压器各结构参数对其工作稳定性的影响规律,并比较了两者间的异同,随后根据工程需要,选取减压器二级阀芯运动速度的样本方差作为稳定性指标,重点研究了某减压器二级阀芯质量、低压腔体积、反馈腔体积及膜片刚度变化对稳定性的影响程度.仿真结果表明,设计人员可以优先减小该减压器的二级阀芯质量或增大膜片刚度从而更快地改善其稳定性,该分析方法可以帮助相关设计人员以最小的代价获得满足工程要求的结果. 相似文献
624.
Guanyi Ma Wei Gao Jinghua Li Yanhong Chen Hua Shen 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
With 4 GPS receivers located in the equatorial anomaly region in southeast China, this paper proposes a grid-based algorithm to determine the GPS satellites and receivers biases, and at the same time to derive the total electron content (TEC) with time resolution of 15 min and spatial resolution of 1° by 3.5° in latitude and longitude. By assuming that the TEC is identical at any point within a given grid block and the biases do not vary within a day, the algorithm arranges unknown biases and TECs with slant path TEC from the 4 receivers’ observations into a set of equations. Then the instrumental biases and the TECs are determined by using the least squares fitting technique. The performance of the method is examined by applying it to the GPS receiver chain observations selected from 16 geomagnetically quiet days in four seasons of 2006. It is found that the fitting agrees with the data very well, with goodness of fit ranging from 0.452 TECU to 1.914 TECU. Having a mean of 0.9 ns, the standard deviations for most of the GPS satellite biases are less than 1.0 ns for the 16 days. The GPS receiver biases are more stable than that of the GPS satellites. The standard deviation in the 4 receiver bias is from 0.370 ns to 0.855 ns, with a mean of 0.5 ns. Moreover, the instrumental biases are highly correlated with those derived from CODE and JPL with independent methods. The typical precision of the derived TEC is 5 TECU by a conservative estimation. These results indicate that the proposed algorithm is valid and qualified for small scale GPS network. 相似文献
625.
Q. Liu Z. Wu M. Zhu W.Q. Xu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
The increase of balloon applications makes it necessary for a comprehensive understanding of the thermal and dynamic performance of scientific balloons. This paper proposed a novel numerical model to investigate the thermal and dynamic characteristics of scientific balloon in both ascending and floating conditions. The novel model consists of a dynamic model and thermal model, the dynamic model was solved numerically by a computer program developed with Matlab/Simulink to calculate the velocity and trajectory, the thermal model was solved by the Fluent program to find out the balloon film temperature distribution and inner Helium gas velocity and temperature field. These models were verified by comparing the numerical results with experimental data. Then the thermal and dynamic behavior of a scientific balloon in a real environment were simulated and discussed in details. 相似文献
626.
Zhengshi Yu Pingyuan Cui Shengying Zhu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
A thorough observability analysis of the Mars entry navigation using radiometric measurements from ground based beacons is performed. This analysis involves the evaluation of the Fisher information matrix which is derived from the maximum likelihood estimation. A series of navigation cases with multiple beacons are investigated, and both range and range-rate measurements are considered. The determinant of Fisher information matrix is used to quantify the observability of navigation system, while the trace of Fisher information matrix is used to determine the lower-bound of estimation errors. For one and two beacon cases, the navigation system is unobservable. However, the eigenvectors of Fisher information matrix give the observable and unobservable component. When three or more beacon measurements are employed, the states of entry vehicle become observable. Some valuable analytic conclusions on the relationship between the geometric configuration of beacons and observability are obtained consequently. Finally, simulation results from two navigation examples indicate that our effort is useful for understanding and assessing the observability of the Mars entry navigation using radiometric measurements. 相似文献
627.
摩擦磨损是飞机柱塞泵典型的渐进性故障,因磨损量难以直接测量,通常采用振动信号进行间接测量.磨损引起的振动信号故障特征微弱,对磨损状态进行准确地识别比较困难.针对上述问题,提出了基于谐波分量边频相对能量和的磨损状态识别方法,该方法对壳体振动信号进行Hilbert包络解调消除高频周期干扰,得到清晰的谐波分量,在各谐波分量的特定边频区间内计算最大能量与平均能量的比值并求和,将该值作为新的特征量来表征柱塞泵的不同磨损状态,利用网格法对边频区间范围寻优.结果表明,边频相对能量和相比传统的特征频率能量对磨损状态的区分度更高,适于磨损状态识别. 相似文献
628.