全文获取类型
收费全文 | 8553篇 |
免费 | 18篇 |
国内免费 | 26篇 |
专业分类
航空 | 3874篇 |
航天技术 | 3089篇 |
综合类 | 34篇 |
航天 | 1600篇 |
出版年
2021年 | 82篇 |
2019年 | 63篇 |
2018年 | 182篇 |
2017年 | 119篇 |
2016年 | 125篇 |
2015年 | 57篇 |
2014年 | 208篇 |
2013年 | 255篇 |
2012年 | 242篇 |
2011年 | 363篇 |
2010年 | 262篇 |
2009年 | 398篇 |
2008年 | 460篇 |
2007年 | 271篇 |
2006年 | 204篇 |
2005年 | 227篇 |
2004年 | 215篇 |
2003年 | 266篇 |
2002年 | 182篇 |
2001年 | 279篇 |
2000年 | 160篇 |
1999年 | 200篇 |
1998年 | 236篇 |
1997年 | 143篇 |
1996年 | 207篇 |
1995年 | 243篇 |
1994年 | 247篇 |
1993年 | 155篇 |
1992年 | 193篇 |
1991年 | 77篇 |
1990年 | 75篇 |
1989年 | 187篇 |
1988年 | 77篇 |
1987年 | 83篇 |
1986年 | 85篇 |
1985年 | 248篇 |
1984年 | 195篇 |
1983年 | 156篇 |
1982年 | 175篇 |
1981年 | 261篇 |
1980年 | 71篇 |
1979年 | 77篇 |
1978年 | 68篇 |
1977年 | 51篇 |
1975年 | 58篇 |
1974年 | 45篇 |
1973年 | 41篇 |
1972年 | 43篇 |
1971年 | 42篇 |
1970年 | 45篇 |
排序方式: 共有8597条查询结果,搜索用时 15 毫秒
71.
T. J. Ponman A. M. Read 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》1993,13(12):361-364
Using data from the Wide Field Camera EUV all-sky survey, we have established upper limits to the EUV flux from a sample of 30 bright, nearby, non-active spiral galaxies. These galaxies were chosen to be those most likely to be detected in the EUV on the basis of (i) low interstellar absorption within our own galaxy, (ii) brightness in other wavebands, (iii) high star formation activity, and (iv) proximity. The derived EUV upper limits are restrictive, and establish for the first time that the EUV flux escaping from galaxies does not constitute a major component of their bolometric luminosity, and in particular that it cannot be the sink for the energy injected into the interstellar medium by supernova explosions, as had been suggested following the failure to detect this power in the X-ray band. 相似文献
72.
Senrad: an advanced wideband air-surveillance radar 总被引:1,自引:0,他引:1
Skolnik M. Linde G. Meads K. 《IEEE transactions on aerospace and electronic systems》2001,37(4):1163-1175
The generic characteristics and performance of an experimental long-range air-surveillance radar, known at the Naval Research Laboratory as Senrad, is described. Its distinguishing feature is that it can operate with simultaneous transmissions over a very wide bandwidth-from 850 to 1400 MHz. The technology and type of experimental radar equipment employed are discussed and examples are given of its performance capabilities obtained by means of very wideband operation. The unusually wide bandwidth of this radar allows 1) improved detection and tracking performance because of the absence of the nulls that are common in the antenna elevation radiation-pattern of a single-frequency radar; 2) moving target indication (MTI) without loss of targets due to blind speeds and without the need for multiple PRFs (pulse repetition frequencies); 3) accurate height finding with a fan-beam radar by taking advantage of the multipath time difference as a function of target height; 4) a form of limited target recognition based on high range-resolution; and 5) a reduction of the effectiveness of electronic countermeasures that can seriously degrade more narrowband radars 相似文献
73.
Bacon B.J. Ostroff A.J. Joshi S.M. 《IEEE transactions on aerospace and electronic systems》2001,37(4):1373-1383
A modified derivation of nonlinear dynamic inversion provides the theoretical underpinnings for a reconfigurable control law for aircraft that have suffered combinations of actuator failures, missing effector surfaces, and aerodynamic changes. The approach makes use of acceleration feedback to extract information pertaining to any aerodynamic change and thus does not require a complete aerodynamic model of the aircraft. The control law does require feedback of effector positions to accommodate actuator dynamics. Both accelerometer and rate gyro failure detection and isolation (FDI) systems are implemented, allowing up to three independent failures for each FDI system as long as they are in different axes. Nonlinear simulation results show that the FDI systems improve the robustness to accelerometer/rate gyro uncertainties. An advanced tailless aircraft model is used to demonstrate the concepts. The simulation includes accelerometer and rate gyro noise and bias, failures due to accelerometers, rate gyros, and actuators, and modeled missing surfaces that cause airplane aerodynamic changes 相似文献
74.
A representative switched-capacitor DC-DC converter topology is presented, circuit operation is explained, and control strategies are identified. State-space averaging is used to analyze steady-state performance and to develop control criteria and design equations. The analytical results are verified by SPICE simulation 相似文献
75.
The Freja ultraviolet imager 总被引:2,自引:0,他引:2
J. S. Murphree R A. King T. Payne K. Smith D. Reid J. Adema B. Gordon R. Wlochowicz 《Space Science Reviews》1994,70(3-4):421-446
Auroral images acquired by satellite instrumentation have proven to be a crucial component of the scientific equiry into the physical processes of the Earth's magnetosphere. TheFreja mission provided an opportunity to extend these measurements into the temporal and spatial regime commonly associated with ground-based optical imagers. Employing the basic procedure used successfully in theViking program allowed image repetition rates of 6 s to be achieved with simultaneous exposure of all pixels within the field-of-view. Typical exposure times of 0.3 s required development of an improved image intensifier system and operational requirements resulted in image formats covering approximately one-third of a spin. Simultaneously exposing two broad-band UV cameras, the instrument generates in its normal operational mode 264.6 kbytes per image pair. Results from initial operations confirm the design approach and suggest such imagers can be routinely included on challenging low cost missions such asFreja. 相似文献
76.
Y. Futaana S. Barabash A. Grigoriev D. Winningham R. Frahm M. Yamauchi R. Lundin 《Space Science Reviews》2006,126(1-4):315-332
As a part of the global plasma environment study of Mars and its response to the solar wind, we have analyzed a peculiar case
of the subsolar energetic neutral atom (ENA) jet observed on June 7, 2004 by the Neutral Particle Detector (NPD) on board
the Mars Express satellite. The “subsolar ENA jet” is generated by the interaction between the solar wind and the Martian
exosphere, and is one of the most intense sources of ENA flux observed in the vicinity of Mars. On June 7, 2004 (orbit 485
of Mars Express), the NPD observed a very intense subsolar ENA jet, which then abruptly decreased within ∼10 sec followed
by quasi-periodic (∼1 min) flux variations. Simultaneously, the plasma sensors detected a solar wind structure, which was
most likely an interplanetary shock surface. The abrupt decrease of the ENA flux and the quasi-periodic flux variations can
be understood in the framework of the global response of the Martian plasma obstacle to the interplanetary shock. The generation
region of the subsolar ENA jet was pushed towards the planet by the interplanetary shock; and therefore, Mars Express went
out of the ENA jet region. Associated global vibrations of the Martian plasma obstacle may have been the cause of the quasi-periodic
flux variations of the ENA flux at the spacecraft location. 相似文献
77.
78.
Hurd W.J. Statman J.I. Vilnrotter V.A. 《IEEE transactions on aerospace and electronic systems》1987,(4):425-437
A new high dynamic global positioning system (GPS) receiver ispresented and its performance characterized by analysis,simulation, and demonstration. The demonstration receiver is abreadboard model capable of tracking a single simulated satellitesignal in pseudorange and range rate. Pseudorange and range rateestimates are made once every 20 ms, using a maximum likelihoodestimator, and are tracked by means of a third-order fadingmemory filter in a feedback configuration. The receiver trackspseudorange with rms errors of under 1 m when subjected tosimulated 50 g, 40 g/s circular trajectories. The tracking thresholdis approximately 28 dB·Hz, which provides 12 dB margin relativethe the minimum specified signal strength, assuming 3.5 dB systemnoise figure and 0 dB antenna gain. 相似文献
79.
M M Saulmon K F Reardon W Z Sadeh 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》1996,18(1-2):289-292
As space missions become longer in duration, the need to recycle waste into useful compounds rises dramatically. This problem can be addressed by the development of Controlled Ecological Life Support Systems (CELSS) (i.e., Engineered Closed/Controlled Eco-Systems (ECCES)), consisting of human and plant modules. One of the waste streams leaving the human module is urine. In addition to the reclamation of water from urine, recovery of the nitrogen is important because it is an essential nutrient for the plant module. A 3-step biological process for the recycling of nitrogenous waste (urea) is proposed. A packed-bed bioreactor system for this purpose was modeled, and the issues of reaction step segregation, reactor type and volume, support particle size, and pressure drop were addressed. Based on minimization of volume, a bioreactor system consisting of a plug flow immobilized urease reactor, a completely mixed flow immobilized cell reactor to convert ammonia to nitrite, and a plug flow immobilized cell reactor to produce nitrate from nitrite is recommended. It is apparent that this 3-step bioprocess meets the requirements for space applications. 相似文献
80.