全文获取类型
收费全文 | 8077篇 |
免费 | 40篇 |
国内免费 | 29篇 |
专业分类
航空 | 3615篇 |
航天技术 | 2819篇 |
综合类 | 30篇 |
航天 | 1682篇 |
出版年
2021年 | 90篇 |
2019年 | 61篇 |
2018年 | 188篇 |
2017年 | 136篇 |
2016年 | 131篇 |
2015年 | 58篇 |
2014年 | 202篇 |
2013年 | 249篇 |
2012年 | 245篇 |
2011年 | 376篇 |
2010年 | 275篇 |
2009年 | 402篇 |
2008年 | 435篇 |
2007年 | 263篇 |
2006年 | 194篇 |
2005年 | 220篇 |
2004年 | 218篇 |
2003年 | 244篇 |
2002年 | 177篇 |
2001年 | 251篇 |
2000年 | 150篇 |
1999年 | 179篇 |
1998年 | 218篇 |
1997年 | 142篇 |
1996年 | 192篇 |
1995年 | 229篇 |
1994年 | 203篇 |
1993年 | 135篇 |
1992年 | 176篇 |
1991年 | 56篇 |
1990年 | 58篇 |
1989年 | 162篇 |
1988年 | 74篇 |
1987年 | 70篇 |
1986年 | 71篇 |
1985年 | 217篇 |
1984年 | 177篇 |
1983年 | 132篇 |
1982年 | 139篇 |
1981年 | 236篇 |
1980年 | 75篇 |
1979年 | 54篇 |
1978年 | 64篇 |
1977年 | 45篇 |
1975年 | 61篇 |
1974年 | 47篇 |
1973年 | 38篇 |
1972年 | 41篇 |
1971年 | 41篇 |
1970年 | 40篇 |
排序方式: 共有8146条查询结果,搜索用时 718 毫秒
251.
A track-while scan (TWS) algorithm is developed for targets in a clutter environment. The problem has been studied using only the position measurements [1, 5-8], but the simulation results have not been satisfactory. Modern processing techniques (FFT processor) ) in air traffic control and surveillance radar receivers provide both position and radial velocity. The radial velocity measurement may be conveniently used in the target-track correlation process, which will reduce the association ambiguity in the clutter environment. t. In the clear environment the algorithm using the position and radial velocity measurements has been treated in [3, 4]. A TWS algorithm, using both position and radial velocity measurements for targets in a clutter environment, is presented here. The algorithm obtained is nonlinear and adaptive. In order to evaluate the improvement due to radial velocity measurement a simulation has been performed on a digital computer. The algorithm was run with and without radial velocity measurements to compare its performances. An improvement was noted especially when the target path included an accelerated portion. 相似文献
252.
Leith E.N. Friesem A.A. Funkhouser A.T. 《IEEE transactions on aerospace and electronic systems》1970,(6):832-840
Coherent optical systems, because of their basic similarity to coherent radar systems, can be used to simulate many of the characteristics of the latter. This paper discusses the use of a coherent optical system for the simulation of the range and azimuth ambiguities that sometimes occur in radar systems. The optical configurations for implementing these simulations are described in detail, and extensive experimental results are presented. 相似文献
253.
An Adaptive Extended Kalman Filter for Target Image Tracking 总被引:1,自引:0,他引:1
254.
H. Borg L. -A. Holmgren B. Hultovist F. Cambou H. Rème A. Bahnsen G. Kremser 《Space Science Reviews》1978,22(5):511-535
Some preliminary new results are presented of the keV plasma experiment on GEOS-1. Electrons and ions have been observed to stream along the magnetic field lines in the dayside magnetosphere from the ionospheric side of the satellite towards the equatorial plane during magnetic storms, with streaming velocities corresponding to a kinetic energy of the order of a keV. The opposite streaming velocity has also been seen, but primarily in the ions only and with a smaller flux ratio for the two opposite directions along the field lines. The transition between the two opposite streaming directions, as seen by the satellite, has been found to occur even in a fraction of a second.In magnetic storm conditions azimuthal asymmetries in ion fluxes corresponding to electric field intensities of several tens of millivolts per meter have been observed. 相似文献
255.
A set of algorithms is presented for finding the best set of K mutually exclusive paths through a trellis of N nodes, with worst-case computation time bounded by N 3log n for a fixed-precision computation. The algorithms are based on a transformation of the K-path trellis problem into an equivalent minimum-cost network flow (MCNF) problem. The approach allows the application of efficient MCNF algorithms, which can obtain optimal solutions orders of magnitude faster than the algorithm proposed by J.K. Wolf et al. (1989). The resulting algorithms extend the practicality of the trellis formulation (in terms of required computations) to multiobject tracking problems with much larger numbers of targets and false alarms. A response by Wolf et al. is included 相似文献
256.
Performance prediction for a detection system employing noncoherent integration is carried out for a chi-square family of fluctuating targets in K -distributed clutter plus noise. The detection performance for Swerling 11 targets in the K -distributed clutter plus noise is compared with that in exponentially correlated Rayleigh clutter. The results show that the performance prediction based on N pulses integrated in clutter plus noise using the K -distributed clutter model may be approximately equivalent to that using the exponentially correlated Rayleigh-distributed clutter model 相似文献
257.
The ordered-statistics (OS) constant false-alarm rate (CFAR) is relatively immune to the presence of interfering targets among the reference cells used to determine the average background. OS CFAR performance in a multitarget environment was previously studied by simulation. The author obtains analytic expressions for the added detection loss, assuming strong interfering targets. The real target is assumed to be a Rayleigh fluctuating target. Numerical examples are included 相似文献
258.
Dabbous T.E. Ahmed N.U. McMillan J.C. Liang D.F. 《IEEE transactions on aerospace and electronic systems》1988,24(1):85-102
A refined stochastic model for the errors of the Loran-C radio navigation aid is described, and it is shown how this model can be used to improve the performance of integrated navigation systems. In addition to the usual propagation errors, Loran-C time of arrival measurements are occasionally plagued with sudden intermittent errors of a particular magnitude and caused by receiver cycle selection errors. These result in sudden large jumps in the calculated position solution. The Loran-C error has been modeled as the sum of a diffusion process, representing the normal propagating errors, and a pure jump process of Poisson type, representing the cycle selection errors. A simple integrated navigation system is then described, based on the Loran-C model and the standard dead reckoning (heading and speed) system model. Assuming that the observed process is governed by a linear stochastic difference equation, a recursive linear unbiased minimum variance filter is developed, from which the Loran-C and dead reckoning errors, and hence position and velocity, can be estimated 相似文献
259.
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
260.
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