全文获取类型
收费全文 | 250篇 |
免费 | 91篇 |
国内免费 | 30篇 |
专业分类
航空 | 216篇 |
航天技术 | 60篇 |
综合类 | 42篇 |
航天 | 53篇 |
出版年
2024年 | 2篇 |
2023年 | 10篇 |
2022年 | 16篇 |
2021年 | 14篇 |
2020年 | 18篇 |
2019年 | 14篇 |
2018年 | 20篇 |
2017年 | 11篇 |
2016年 | 19篇 |
2015年 | 21篇 |
2014年 | 23篇 |
2013年 | 15篇 |
2012年 | 14篇 |
2011年 | 19篇 |
2010年 | 16篇 |
2009年 | 6篇 |
2008年 | 18篇 |
2007年 | 8篇 |
2006年 | 10篇 |
2005年 | 2篇 |
2004年 | 2篇 |
2003年 | 8篇 |
2002年 | 4篇 |
2001年 | 5篇 |
2000年 | 6篇 |
1999年 | 4篇 |
1998年 | 14篇 |
1997年 | 11篇 |
1996年 | 10篇 |
1995年 | 6篇 |
1994年 | 2篇 |
1993年 | 9篇 |
1992年 | 1篇 |
1990年 | 4篇 |
1989年 | 2篇 |
1987年 | 1篇 |
1986年 | 2篇 |
1985年 | 1篇 |
1983年 | 1篇 |
1980年 | 1篇 |
1969年 | 1篇 |
排序方式: 共有371条查询结果,搜索用时 15 毫秒
81.
The actual boundary conditions of cantilever-like structures might be non-ideally clamped in engineering practice, and they can also vary with time due to damage or aging. Precise modelling of boundary conditions, in which both the boundary stiffness and the boundary mass should be modelled correctly, might be one of the most significant aspects in dynamic analysis and testing for such structures. However, only the boundary stiffness was considered in the most existing methods. In this paper, a boundary condition modelling and identification method for cantilever-like structures is proposed to precisely model both the boundary stiffness and the boundary mass using sensitivity analysis of natural frequencies. The boundary conditions of a cantilever-like structure can be parameterized by constant mass, constant rotational inertia,constant translational stiffness, and constant rotational stiffness. The relationship between natural frequencies and boundary parameters is deduced according to the vibration equation for the lateral vibration of a non-uniform beam. Then, an iterative identification formulation is established using the sensitivity analysis of natural frequencies with respect to the boundary parameters. The regularization technique is also used to solve the potential ill-posed problem in the identification procedure.Numerical simulations and experiments are performed to validate the feasibility and accuracy of the proposed method. Results show that the proposed method can be utilized to precisely model the boundary parameters of a cantilever-like structure. 相似文献
82.
The Magnetospheric Multiscale Magnetometers 总被引:2,自引:0,他引:2
C. T. Russell B. J. Anderson W. Baumjohann K. R. Bromund D. Dearborn D. Fischer G. Le H. K. Leinweber D. Leneman W. Magnes J. D. Means M. B. Moldwin R. Nakamura D. Pierce F. Plaschke K. M. Rowe J. A. Slavin R. J. Strangeway R. Torbert C. Hagen I. Jernej A. Valavanoglou I. Richter 《Space Science Reviews》2016,199(1-4):189-256
The success of the Magnetospheric Multiscale mission depends on the accurate measurement of the magnetic field on all four spacecraft. To ensure this success, two independently designed and built fluxgate magnetometers were developed, avoiding single-point failures. The magnetometers were dubbed the digital fluxgate (DFG), which uses an ASIC implementation and was supplied by the Space Research Institute of the Austrian Academy of Sciences and the analogue magnetometer (AFG) with a more traditional circuit board design supplied by the University of California, Los Angeles. A stringent magnetic cleanliness program was executed under the supervision of the Johns Hopkins University’s Applied Physics Laboratory. To achieve mission objectives, the calibration determined on the ground will be refined in space to ensure all eight magnetometers are precisely inter-calibrated. Near real-time data plays a key role in the transmission of high-resolution observations stored on board so rapid processing of the low-resolution data is required. This article describes these instruments, the magnetic cleanliness program, and the instrument pre-launch calibrations, the planned in-flight calibration program, and the information flow that provides the data on the rapid time scale needed for mission success. 相似文献
83.
84.
85.
目前对飞机起落架低频刹车耦合振动问题的研究主要停留在考虑轮胎参数影响的起落架纵向单自由度振动特性分析,对于多自由度低频刹车耦合振动的特性研究不足。基于Simcenter 3D 动力学分析软件建立双轮支柱式起落架刚柔耦合整机滑跑刹车分析模型,研究轮胎竖向刚度和侧偏刚度对双轮支柱式起落架低频刹车纵向、横向和扭转的多自由度耦合振动的影响。结果表明:轮胎的竖向刚度对起落架横向和扭转方向上的振动影响较大,轮胎竖向刚度变化33%,横向和扭转方向上的振动变化5% 左右;轮胎的侧偏刚度对起落架低频刹车横向上的振动影响较大,轮胎侧偏刚度变化33%,横向上的振动变化15% 左右。 相似文献
86.
87.
In numerous practical situations a large array of sensors is required, especially for improving the system ability to detect and track moving sources. However, the array performance is strongly affected by the lack of stationarity of the impinging signals. The use of a large array of sensors allow us to perform the source localization by using the wavefront curvature. The analysis of the range estimates based on the wavefront curvature have been thoroughly performed by various authors but, to our knowledge, is restricted to the case of fixed sources. The study of the effects of source motion for range estimation (Section III) and source detection (Section V) constitutes an important part of this work. This study reveals that the array performance can be far from the expected values, especially for large array. Therefore, the robustness of a direct processing of the whole sensor array is very questionable. The computational burden constitutes another serious drawback of this (direct) approach. The use of partitioned processings (Sections IV and VI) seems thus quite promising even if (and perhaps because) it is not optimal so as to fulfil the computation cost and robustness requirements. The performance of such processings for estimating the range of moving sources is presented 相似文献
88.
目前,不同机构提供的GNSS实时服务产品性能存在差异。为了全面揭示实时服务产品的性能,为系统服务和用户应用提供参考,统计了各实时服务产品的历元完整率及卫星数量,基于实时轨道和钟差恢复方法,比较分析了产品精度,并评估了产品定位性能。研究结果表明:正常情况下,实时服务产品的历元完整率较高,基本可保持在95%以上,所提供系统的卫星数量保持稳定且充足。对于GPS,各机构卫星实时轨道平均精度基本一致,约为3cm,实时钟差精度略有差别。对于其他GNSS,不同机构产品精度存在差别。利用实时服务产品进行GPS实时精密单点定位的平面精度优于10cm,高程精度优于20cm。相对于GPS单系统,多系统联合定位精度基本一致,但收敛速度明显提升。 相似文献
89.
Mg—Li合金的均化制度研究 总被引:2,自引:0,他引:2
对Mg-Li合金的均匀化工艺及制度进行了研究。实验表明,铸锭包覆铝箔的方法可以使均化过程顺利进行;确定了Mg-Li二元合金的均化制度为300℃×24h,添加合金元素的Mg-7Li-14Zn三元以上的合金均化制度确定为300℃×36h。 相似文献
90.
基于姿态敏感器的地球同步轨道卫星自主导航研究 总被引:1,自引:0,他引:1
本文提出了一种基于姿态敏感器的地球同步轨道卫星自主导航方法,作为解决未来高轨道卫星自主运行的先决条件。在整个系统中,以包含摄动项的HILL 方程作为状态方程,根据由姿态敏感器给出的卫星本体相对于地球和另外两个空间天体的方位,推导出测量方程,进而用简化的推广 Kalman 滤波算法进行状态估计。仿真表明,该方法收敛速度快,精度较高,是一种可行的地球同步轨道卫星自主导航方法。 相似文献