全文获取类型
收费全文 | 7615篇 |
免费 | 34篇 |
国内免费 | 14篇 |
专业分类
航空 | 3759篇 |
航天技术 | 2450篇 |
综合类 | 27篇 |
航天 | 1427篇 |
出版年
2021年 | 62篇 |
2019年 | 42篇 |
2018年 | 221篇 |
2017年 | 167篇 |
2016年 | 113篇 |
2015年 | 65篇 |
2014年 | 169篇 |
2013年 | 182篇 |
2012年 | 212篇 |
2011年 | 348篇 |
2010年 | 269篇 |
2009年 | 402篇 |
2008年 | 452篇 |
2007年 | 271篇 |
2006年 | 158篇 |
2005年 | 234篇 |
2004年 | 181篇 |
2003年 | 243篇 |
2002年 | 138篇 |
2001年 | 248篇 |
2000年 | 126篇 |
1999年 | 160篇 |
1998年 | 189篇 |
1997年 | 131篇 |
1996年 | 156篇 |
1995年 | 223篇 |
1994年 | 202篇 |
1993年 | 114篇 |
1992年 | 163篇 |
1991年 | 79篇 |
1990年 | 68篇 |
1989年 | 160篇 |
1988年 | 73篇 |
1987年 | 76篇 |
1986年 | 69篇 |
1985年 | 181篇 |
1984年 | 157篇 |
1983年 | 143篇 |
1982年 | 153篇 |
1981年 | 190篇 |
1980年 | 64篇 |
1979年 | 60篇 |
1978年 | 56篇 |
1977年 | 45篇 |
1976年 | 44篇 |
1975年 | 55篇 |
1974年 | 45篇 |
1973年 | 40篇 |
1972年 | 52篇 |
1971年 | 38篇 |
排序方式: 共有7663条查询结果,搜索用时 109 毫秒
841.
842.
Robert A. Goehlich Jay K. AndersonNathan N. Harrold Joseph A. BemisMike T. Nettleingham Joshua M. CobinBradley R. Zimmerman Ben L. AvniMichael D. Gonyea Nicholas Y. Ilchena 《Space Policy》2013
This article sheds light on the key player needed for any space tourism adventure: the pilot who flies the spacecraft. The paper addresses the potential benefits of including a pilot at the controls when designing a space tourism spacecraft. It examines the basic qualifications and advanced skills required of space tourism pilots and discusses key training requirements for selected pilots and space pilots' pay and benefits. In addition, the research concludes that, just as the pioneers of passenger transport in aviation entertained and captured the interest of their passengers, the space pilot should have the skills of a tour guide. 相似文献
843.
Deborah L. Domingue Clark R. Chapman Rosemary M. Killen Thomas H. Zurbuchen Jason A. Gilbert Menelaos Sarantos Mehdi Benna James A. Slavin David Schriver Pavel M. Trávníček Thomas M. Orlando Ann L. Sprague David T. Blewett Jeffrey J. Gillis-Davis William C. Feldman David J. Lawrence George C. Ho Denton S. Ebel Larry R. Nittler Faith Vilas Carle M. Pieters Sean C. Solomon Catherine L. Johnson Reka M. Winslow Jörn Helbert Patrick N. Peplowski Shoshana Z. Weider Nelly Mouawad Noam R. Izenberg William E. McClintock 《Space Science Reviews》2014,181(1-4):121-214
Mercury’s regolith, derived from the crustal bedrock, has been altered by a set of space weathering processes. Before we can interpret crustal composition, it is necessary to understand the nature of these surface alterations. The processes that space weather the surface are the same as those that form Mercury’s exosphere (micrometeoroid flux and solar wind interactions) and are moderated by the local space environment and the presence of a global magnetic field. To comprehend how space weathering acts on Mercury’s regolith, an understanding is needed of how contributing processes act as an interactive system. As no direct information (e.g., from returned samples) is available about how the system of space weathering affects Mercury’s regolith, we use as a basis for comparison the current understanding of these same processes on lunar and asteroidal regoliths as well as laboratory simulations. These comparisons suggest that Mercury’s regolith is overturned more frequently (though the characteristic surface time for a grain is unknown even relative to the lunar case), more than an order of magnitude more melt and vapor per unit time and unit area is produced by impact processes than on the Moon (creating a higher glass content via grain coatings and agglutinates), the degree of surface irradiation is comparable to or greater than that on the Moon, and photon irradiation is up to an order of magnitude greater (creating amorphous grain rims, chemically reducing the upper layers of grains to produce nanometer-scale particles of metallic iron, and depleting surface grains in volatile elements and alkali metals). The processes that chemically reduce the surface and produce nanometer-scale particles on Mercury are suggested to be more effective than similar processes on the Moon. Estimated abundances of nanometer-scale particles can account for Mercury’s dark surface relative to that of the Moon without requiring macroscopic grains of opaque minerals. The presence of nanometer-scale particles may also account for Mercury’s relatively featureless visible–near-infrared reflectance spectra. Characteristics of material returned from asteroid 25143 Itokawa demonstrate that this nanometer-scale material need not be pure iron, raising the possibility that the nanometer-scale material on Mercury may have a composition different from iron metal [such as (Fe,Mg)S]. The expected depletion of volatiles and particularly alkali metals from solar-wind interaction processes are inconsistent with the detection of sodium, potassium, and sulfur within the regolith. One plausible explanation invokes a larger fine fraction (grain size <45 μm) and more radiation-damaged grains than in the lunar surface material to create a regolith that is a more efficient reservoir for these volatiles. By this view the volatile elements detected are present not only within the grain structures, but also as adsorbates within the regolith and deposits on the surfaces of the regolith grains. The comparisons with findings from the Moon and asteroids provide a basis for predicting how compositional modifications induced by space weathering have affected Mercury’s surface composition. 相似文献
844.
The ionosphere of Mars has been explored mostly with the radio occultation experiment onboard Mariners 6, 7, 9; Mars 2, 3, 4, 6; Viking 1, 2, and more recently on Mars Global Surveyor (MGS) and Mars Express (MEX). In addition to the radio occultation experiment, MEX also carried Mars Advanced Radar for the Subsurface and Ionosphere Sounding (MARSIS) experiment which provided electron density profiles well above the main ionospheric peak. The atmosphere of Mars was measured directly by the neutral mass spectrometer onboard Viking 1 and 2 Landers. Later, an accelerometer and radio occultation experiment on MGS provided large data sets of atmospheric density at various locations in the upper and lower atmospheres of Mars, respectively. In this paper we review results of these upper and lower atmospheric/ionospheric measurements. Results of these measurements have been compared with theoretical models by several workers; therefore, we also review various atmospheric and ionospheric models of Mars. 相似文献
845.
Coronal holes are the coolest and darkest regions of the upper solar atmosphere, as observed both on the solar disk and above the solar limb. Coronal holes are associated with rapidly expanding open magnetic fields and the acceleration of the high-speed solar wind. During the years of the solar minima, coronal holes are generally confined to the Sun??s polar regions, while at solar maxima they can also be found at lower latitudes. Waves, observed via remote sensing and detected in-situ in the wind streams, are most likely responsible for the wind and several theoretical models describe the role of MHD waves in the acceleration of the fast solar wind. This paper reviews the observational evidences of detection of propagating waves in these regions. The characteristics of the waves, like periodicities, amplitude, speed provide input parameters and also act as constraints on theoretical models of coronal heating and solar wind acceleration. 相似文献
846.
Dynamics of a satellite-stabilizer system is studied. It is supposed that there is a viscous friction in a hinge connecting
two bodies, but there is no elasticity. The attitude motion in a plane of circular orbit is considered, and parameters are
determined, at which natural oscillations near a stable equilibrium position in the orbital coordinate system are damped out
most rapidly. The rate of transient processes is estimated by a value of the degree of stability of linearized equations of
motion. The optimization of the degree of stability is sequentially performed in dimensionless damping coefficient (the first
stage) and in inertial system parameters (the second stage). The result of the first stage is the partition of system parameter
space into the regions, in each of which the maximum of the degree of stability is reached on a particular configuration of
roots of the characteristic equation. It is shown at the second stage that the global maximum is reached at two points of
parameter space, where one of system bodies degenerates into a plate, and the characteristic equation has four equal real
roots. 相似文献
847.
Ovshinsky S.R. Dhar S.K. Fetcenko M.A. Corrigan D.A. Reichman B. Young K. Fierro C. Venkatesan S. Gifford P. Koch J. 《Aerospace and Electronic Systems Magazine, IEEE》1999,14(5):17-23
While Ovonic NiMH batteries are already in high volume commercial production for portable applications, advances in materials technology have enabled performance improvements in specific energy (100 Wh/kg), specific power (600-1000 W/kg), high temperature operation, charge retention, and voltage stability. Concurrent with technology advances, Ovonic NiMH batteries have established performance and commercial milestones in electric vehicles, hybrid electric vehicles, as well as scooter, motorcycle and bicycle applications. As important as these advances, significant manufacturing cost reductions have also occurred which allow continued growth of NiMH technology. In this paper, advances in performance, applications and cost reduction are discussed with particular emphasis on the improved proprietary metal hydride and nickel hydroxide materials that make such advances possible 相似文献
848.
849.
The dynamics of the rotational motion of a satellite, moving in the central Newtonian force field under the influence of gravitational and aerodynamic torques, is investigated. The paper proposes a method for determining all equilibrium positions (equilibrium orientations) of a satellite in the orbital coordinate system for specified values of aerodynamic torque and the major central moments of inertia; the sufficient conditions for their existence are obtained. For each equilibrium orientation the sufficient stability conditions are obtained using the generalized energy integral as the Lyapunov function. The detailed numerical analysis of the regions where the stability conditions of the equilibrium positions are satisfied is carried out depending on four dimensionless parameters of the problem. It is shown that, in the general case, the number of satellite’s equilibrium positions, for which the sufficient stability conditions are satisfied, varies from 4 to 2 with an increase in the value of the aerodynamic torque magnitude. 相似文献
850.
J. B. Blake B. H. Mauk D. N. Baker P. Carranza J. H. Clemmons J. Craft W. R. Crain A. Crew Y. Dotan J. F. Fennell R. H. Friedel L. M. Friesen F. Fuentes R. Galvan C. Ibscher A. Jaynes N. Katz M. Lalic A. Y. Lin D. M. Mabry T. Nguyen C. Pancratz M. Redding G. D. Reeves S. Smith H. E. Spence J. Westlake 《Space Science Reviews》2016,199(1-4):309-329