全文获取类型
收费全文 | 3687篇 |
免费 | 746篇 |
国内免费 | 684篇 |
专业分类
航空 | 2553篇 |
航天技术 | 923篇 |
综合类 | 515篇 |
航天 | 1126篇 |
出版年
2024年 | 13篇 |
2023年 | 47篇 |
2022年 | 127篇 |
2021年 | 125篇 |
2020年 | 142篇 |
2019年 | 125篇 |
2018年 | 114篇 |
2017年 | 109篇 |
2016年 | 120篇 |
2015年 | 163篇 |
2014年 | 212篇 |
2013年 | 209篇 |
2012年 | 252篇 |
2011年 | 285篇 |
2010年 | 273篇 |
2009年 | 290篇 |
2008年 | 225篇 |
2007年 | 224篇 |
2006年 | 203篇 |
2005年 | 171篇 |
2004年 | 121篇 |
2003年 | 130篇 |
2002年 | 166篇 |
2001年 | 152篇 |
2000年 | 99篇 |
1999年 | 146篇 |
1998年 | 134篇 |
1997年 | 98篇 |
1996年 | 94篇 |
1995年 | 79篇 |
1994年 | 83篇 |
1993年 | 75篇 |
1992年 | 55篇 |
1991年 | 66篇 |
1990年 | 52篇 |
1989年 | 46篇 |
1988年 | 35篇 |
1987年 | 18篇 |
1986年 | 14篇 |
1985年 | 3篇 |
1984年 | 4篇 |
1983年 | 4篇 |
1982年 | 3篇 |
1981年 | 5篇 |
1980年 | 1篇 |
1978年 | 1篇 |
1975年 | 1篇 |
1974年 | 1篇 |
1965年 | 1篇 |
1900年 | 1篇 |
排序方式: 共有5117条查询结果,搜索用时 519 毫秒
661.
以苏通大桥为研究背景,通过专门研制的一套测压装置,利用测压法对苏通大桥主梁断面气动导纳进行了现场实测研究,并将现场实测结果与风洞实验结果及Sears函数进行了对比研究。结果表明:现场实测结果与风洞实验结果接近,与Sears函数有交叉,在低频范围内远小于Sears函数,在高频范围内逐渐与Sears函数靠拢,表明对于气动导纳来说,风洞实验结果是可靠的,且传统上利用Sears函数代替气动导纳函数进行桥梁结构抖振响应分析时得出的结果将过于保守,因此,对大跨桥梁进行抖振响应分析时,应针对气动导纳函数进行专门的实验研究。 相似文献
662.
J. B. Blake P. A. Carranza S. G. Claudepierre J. H. Clemmons W. R. Crain Jr. Y. Dotan J. F. Fennell F. H. Fuentes R. M. Galvan J. S. George M. G. Henderson M. Lalic A. Y. Lin M. D. Looper D. J. Mabry J. E. Mazur B. McCarthy C. Q. Nguyen T. P. O’Brien M. A. Perez M. T. Redding J. L. Roeder D. J. Salvaggio G. A. Sorensen H. E. Spence S. Yi M. P. Zakrzewski 《Space Science Reviews》2013,179(1-4):383-421
This paper describes the Magnetic Electron Ion Spectrometer (MagEIS) instruments aboard the RBSP spacecraft from an instrumentation and engineering point of view. There are four magnetic spectrometers aboard each of the two spacecraft, one low-energy unit (20–240 keV), two medium-energy units (80–1200 keV), and a high-energy unit (800–4800 keV). The high unit also contains a proton telescope (55 keV–20 MeV). The magnetic spectrometers focus electrons within a selected energy pass band upon a focal plane of several silicon detectors where pulse-height analysis is used to determine if the energy of the incident electron is appropriate for the electron momentum selected by the magnet. Thus each event is a two-parameter analysis, an approach leading to a greatly reduced background. The physics of these instruments are described in detail followed by the engineering implementation. The data outputs are described, and examples of the calibration results and early flight data presented. 相似文献
663.
664.
设计了一种吸气式面对称高超声速飞行器,针对进气道性能,分别在两座风洞开展通流试验研究。针对第1次风洞试验大攻角状态(α=8°)测量值偏离线性的问题,辅助采用数值模拟手段分析原因,并对试验方案进行改进设计,解决了首次试验出现的问题。结果显示,在典型状态(Ma=5~6)下,进气道起动正常,性能良好,具有一定的抗侧滑能力;随来流马赫数增加,进气道流量系数增大,总压恢复系数减小,计算结果和试验结果一致;试验结果和数值计算的差异主要表现为基本测压方案α>4°后,流量系数和总压恢复系数出现严重的非线性。数值模拟结果表明,主要原因为模型支撑方式及测压方式所引起的偏差,通过改进试验方案,解决了大攻角状态下测量值偏离正常趋势的问题。 相似文献
665.
Xi Lin Xiaohua Deng Zhigang Yuan Meng Zhou Shiyou Li Ye Pang 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
We study the structure and kinetic properties of slow-mode shocks near the plasma sheet boundary layer (PSBL) associated with magnetic reconnection by Cluster observation. The presence of slow-mode shocks is confirmed by traditional Rankine–Hugoniot (RH) analysis and Monte-Carlo shock fitting method. The Walén analysis, applied to the tailward flow associated with slow-mode shocks, also supports that plasma was accelerated across a Petschek-type slow-mode shock connected to the diffusion region. Back-streaming ions were observed on the shock layer, and cold ions were accelerated and heated by slow-mode shocks. In addition, whistler and electrostatic solitary waves were observed around the slow-mode shocks. These waves might be excited by the observed field-aligned electron beams near the shocks. 相似文献
666.
Dynamic characteristics analysis of deployable space structures considering joint clearance 总被引:1,自引:0,他引:1
The clearance in joints influences the dynamic stability and the performance of deployable space structures (DSS). A virtual experimental modal analysis (VEMA) method is proposed to deal with the effects of joint clearance and link flexibility on the dynamic characteristics of the DSS in this paper. The focus is on the finite element modeling of the clearance joint, VEMA and the modal parameters identification of the DSS. The finite element models (FEM) of the clearance joint and the deployable structure are established in ANSYS. The transient dynamic analysis is conducted to provide the time history data of excitation and response for the VEMA. The fast Fourier transform (FFT) technique is used to transform the data from time domain to frequency domain. The frequency response function is calculated to identify the modal parameters of the deployable structure. Experimental verification is provided to indicate the VEMA method is both a cost and time efficient approach to obtain the dynamic characteristics of the DSS. Finally, we analyze the effects of clearance size and gravity on the dynamic characteristics of the DSS. The analysis results indicate that the joint clearance and gravity strongly influence the dynamic characteristics of the DSS. 相似文献
667.
Robust speed sensorless induction motor drive 总被引:1,自引:0,他引:1
Faa-Jeng Lin Rong-Jong Wai Pao-Chuan Lin 《IEEE transactions on aerospace and electronic systems》1999,35(2):566-578
A speed sensorless induction motor (IM) drive with robust control characteristics is introduced. First, a speed observation system, which is insensitive to the variations of motor parameters, is derived based on the concept of sliding mode. Next, an integral-proportional (IP) speed controller using the estimated speed signal is designed to stabilize the speed loop. Then, to preserve the robust control performance under parameter variations and external load disturbance, an adaptive uncertainty observer with feedforward control is proposed. The adaptive uncertainty observer is implemented to estimate the lump of uncertainty of the controlled plant. To increase the accuracy of the estimated values, the speed observation system is implemented using a digital signal processor (DSP) with a high sampling rate 相似文献
668.
669.
本文介绍了配料生产过程中单片机控制系统的硬件结构及软件流程。由于硬件和软件设计上都采用了模块化的结构,所以便于安装调试,整个系统可推广到诸如水泥、矿产、食品加工等生产中。 相似文献
670.
New Horizons Mission Design 总被引:1,自引:0,他引:1
In the first mission to Pluto, the New Horizons spacecraft was launched on January 19, 2006, and flew by Jupiter on February 28, 2007, gaining a significant speed boost from Jupiter’s gravity assist. After a 9.5-year journey, the spacecraft will encounter Pluto on July 14, 2015, followed by an extended mission to the Kuiper Belt objects for the first time. The mission design for New Horizons went through more than five years of numerous revisions and updates, as various mission scenarios regarding routes to Pluto and launch opportunities were investigated in order to meet the New Horizons mission’s objectives, requirements, and goals. Great efforts have been made to optimize the mission design under various constraints in each of the key aspects, including launch window, interplanetary trajectory, Jupiter gravity-assist flyby, Pluto–Charon encounter with science measurement requirements, and extended mission to the Kuiper Belt and beyond. Favorable encounter geometry, flyby trajectory, and arrival time for the Pluto–Charon encounter were found in the baseline design to enable all of the desired science measurements for the mission. The New Horizons mission trajectory was designed as a ballistic flight from Earth to Pluto, and all energy and the associated orbit state required for arriving at Pluto at the desired time and encounter geometry were computed and specified in the launch targets. The spacecraft’s flight thus far has been extremely efficient, with the actual trajectory error correction ΔV being much less than the budgeted amount. 相似文献