全文获取类型
收费全文 | 9868篇 |
免费 | 16篇 |
国内免费 | 27篇 |
专业分类
航空 | 4686篇 |
航天技术 | 3241篇 |
综合类 | 200篇 |
航天 | 1784篇 |
出版年
2021年 | 91篇 |
2019年 | 57篇 |
2018年 | 189篇 |
2017年 | 119篇 |
2016年 | 129篇 |
2015年 | 56篇 |
2014年 | 204篇 |
2013年 | 260篇 |
2012年 | 268篇 |
2011年 | 400篇 |
2010年 | 275篇 |
2009年 | 433篇 |
2008年 | 458篇 |
2007年 | 274篇 |
2006年 | 198篇 |
2005年 | 233篇 |
2004年 | 244篇 |
2003年 | 293篇 |
2002年 | 292篇 |
2001年 | 376篇 |
2000年 | 187篇 |
1999年 | 232篇 |
1998年 | 284篇 |
1997年 | 174篇 |
1996年 | 253篇 |
1995年 | 303篇 |
1994年 | 284篇 |
1993年 | 171篇 |
1992年 | 223篇 |
1991年 | 92篇 |
1990年 | 101篇 |
1989年 | 225篇 |
1988年 | 101篇 |
1987年 | 101篇 |
1986年 | 99篇 |
1985年 | 276篇 |
1984年 | 224篇 |
1983年 | 183篇 |
1982年 | 196篇 |
1981年 | 306篇 |
1980年 | 95篇 |
1979年 | 83篇 |
1978年 | 95篇 |
1977年 | 68篇 |
1976年 | 61篇 |
1975年 | 84篇 |
1974年 | 73篇 |
1972年 | 80篇 |
1971年 | 69篇 |
1970年 | 60篇 |
排序方式: 共有9911条查询结果,搜索用时 265 毫秒
321.
322.
The Galileo spacecraft was launched by the Space Shuttle Atlantis on October 18, 1989. A two-stage Inertial Upper Stage propelled Galileo out of Earth parking orbit to begin its 6-year interplanetary transfer to Jupiter. Galileo has already received two gravity assists: from Venus on February 10, 1990 and from Earth on December 8, 1990. After a second gravity-assist flyby of Earth on December 8, 1992, Galileo will have achieved the energy necessary to reach Jupiter. Galileo's interplanetary trajectory includes a close flyby of asteroid 951-Gaspra on October 29, 1991, and, depending on propellant availability and other factors, there may be a second asteroid flyby of 243-Ida on August 28, 1993. Upon arrival at Jupiter on December 7, 1995, the Galileo Orbiter will relay data back to Earth from an atmospheric Probe which is released five months earlier. For about 75 min, data is transmitted to the Orbiter from the Probe as it descends on a parachute to a pressure depth of 20–30 bars in the Jovian atmosphere. Shortly after the end of Probe relay, the Orbiter ignites its rocket motor to insert into orbit about Jupiter. The orbital phase of the mission, referred to as the satellite tour, lasts nearly two years, during which time Galileo will complete 10 orbits about Jupiter. On each of these orbits, there will be a close encounter with one of the three outermost Galilean satellites (Europa, Ganymede, and Callisto). The gravity assist from each satellite is designed to target the spacecraft to the next encounter with minimal expenditure of propellant. The nominal mission is scheduled to end in October 1997 when the Orbiter enters Jupiter's magnetotail.List of Acronyms ASI
Atmospheric Structure Instrument
- EPI
Energetic Particles Instrument
- HGA
High Gain Antenna
- IUS
Inertial Upper Stage
- JOI
Jupiter Orbit Insertion
- JPL
Jet Propulsion Laboratory
- LRD
Lightning and Radio Emissions Detector
- NASA
National Aeronautics and Space Administration
- NEP
Nephelometer
- NIMS
Near-Infrared Mapping Spectrometer
- ODM
Orbit Deflection Maneuver
- OTM
Orbit Trim Maneuver
- PJR
Perijove Raise Maneuver
- PM
Propellant Margin
- PDT
Pacific Daylight Time
- PST
Pacific Standard Time
- RPM
Retropropulsion Module
- RRA
Radio Relay Antenna
- SSI
Solid State Imaging
- TCM
Trajectory Correction Maneuver
- UTC
Universal Time Coordinated
- UVS
Ultraviolet Spectrometer
- VEEGA
Venus-Earth-Earth Gravity Assist 相似文献
323.
Efron A.J. Swaszek P.E. Tufts D.W. 《IEEE transactions on aerospace and electronic systems》1992,28(4):932-943
A detector which is designed to operate in a correlated Gaussian-plus-impulsive-noise environment is presented. The detector whitens the data robustly and then uses a two-sided threshold test to determine the presence of impulsive samples. The impulsive samples are discarded, and the remaining samples are used to detect the presence or absence of a signal using a matched filter. An approximate analysis is presented, and simulations are used to demonstrate the effectiveness of this approach 相似文献
324.
Gawron T.E. Klembowski W. Pikielny J. Jakubiak A. Wojtkiewicz A. Czyz Z.H. Tuszynski M. Centkowski G. 《IEEE transactions on aerospace and electronic systems》1991,27(5):748-783
Polish radar research and development since 1953 is reviewed, covering the development and production of surveillance radars, height finders, tracking radars, air traffic control (ATC) radars and systems, and marine and Doppler radars. Some current work, including an L-band ATC radar for enroute control, a weather channel for primary surveillance radar, signal detection in non-Gaussian clutter, adaptive MTI filters and postdetection filtering, and a basic approach to radar polarimetry, is examined.<> 相似文献
325.
326.
The equations of motion of a momentum biased spacecraft are derived in a general form. The spacecraft is assumed to be orbiting in a near-elliptical orbit. An aerodynamic torque model which accounts for the atmospheric superrotation is assumed. The equilibrium attitude angles are obtained in terms of modified Bessel functions. Analytic expressions for the long-term motion of the momentum biased axis are derived for special cases. The analysis is applicable to the Magsat mission. 相似文献
327.
A Fast Beamforming Algorithm for Large Arrays 总被引:3,自引:0,他引:3
This beamforming algorithm is written specifically for array radars in which the number of array elements K is very large compared with the number of jammers L the radar is designed to suppress. It uses a set of M noise vectors to construct a basis for the jammer component of the antenna output vectors. The component of the quiescent weight vector orthogonal to each basis vector is calculated, renormalized to unit length, and identified as the adapted weight vector. This algorithm is effective in the suppression of many types of jammers. The number of noise samples M required in the construction of the adapted weight vector is approximately equal to L. In the special case of L narrowband noise jammers, for example, a choice of M = L usually reduces the receiver output jammer power to a few dBs above the white noise background. It is permissible to have M相似文献
328.
GTD Terrain Reflection Model Applied to ILS Glide Scope 总被引:1,自引:0,他引:1
Luebbers R. Ungvichian V. Mitchell L. 《IEEE transactions on aerospace and electronic systems》1982,(1):11-20
The capability of calculating the reflection of electromagnetic signals from uneven terrain has many applications. One of these is the determination of instrument landing system (ILS) glide slope performance. For this application the wavelength is approximately 1 m, incidence angles are usually near grazing, and the fields are horizontally polarized, so that gross irregularities such as dropoffs and hills are more important than surface roughness. Past approaches used to calculate the ground reflections for this application have been three-dimensional physical optics models which were very cumbersome and time consuming and which neglected important diffraction and shadowing phenomenon; a two-dimensional physical optics model which was faster than the three-dimensional models but ignored many shadowing and transverse terrain variation effects; and a half-plane diffraction model which is applicable only to a specified type of terrain geometry. In this paper a terrain reflection model based on the geometrical theory of diffraction (GTD) is described which can accommodate any piecewise linear terrain profile, requires less computer time than the physical optics models, is capable of including transverse terrain effects, and determines the reflected fields with all important diffraction and blockage effects included. 相似文献
329.
The performance of a least mean square (LMS) adaptive array in the presence of a pulsed interference signal is examined. It is shown that a pulsed interference signal has two effects. First, it causes the array to modulate the desired signal envelope (but not its phase). Second, it causes the array output signal-to-interferenceplus-noise ratio (SINR) to vary with time. The desired signal modulation is evaluated as a function of signal arrival angles, powers and interference pulse-repetition frequency (PRF) and pulsewidth. It is shown that the signal modulation is small except when the interference arrives close to the desired signal. To evaluate the effect of the time-varying SINR, it is assumed that the array is used in a differential phase-shift keyed (DPSK) communication system. It is shown that the SINR variation causes a noticeable but not disastrous increase in the bit error probability. 相似文献
330.
Methods are discussed for establishing the optical identification of X ray sources in the medium and deep X-ray surveys of the Einstein Observatory. Of the 63 X-ray sources with a statistical significance of 5 in the medium survey (Maccacaro et al. 1981), optical identification work is summarized for 51, of which identifications have been made with 30 active galactic nuclei. The optical properties of some of these X-ray selected objects are briefly discussed.The Einstein deep survey of Pavo (Griffiths et al. 1981) is used to illustrate the problems and methods used for securing optical identifications for X-ray sources in the deep survey fields. Identifications have been made with 4 QSOs at the bright end of the optical candidate distribution (together with 3 G stars) and it is shown that a further 7 fainter objects are also likely to be QSOs. 相似文献