全文获取类型
收费全文 | 113篇 |
免费 | 2篇 |
国内免费 | 4篇 |
专业分类
航空 | 49篇 |
航天技术 | 37篇 |
航天 | 33篇 |
出版年
2021年 | 5篇 |
2019年 | 6篇 |
2018年 | 10篇 |
2017年 | 4篇 |
2016年 | 1篇 |
2015年 | 1篇 |
2014年 | 10篇 |
2013年 | 18篇 |
2012年 | 2篇 |
2011年 | 7篇 |
2010年 | 3篇 |
2009年 | 5篇 |
2008年 | 3篇 |
2007年 | 2篇 |
2006年 | 1篇 |
2005年 | 4篇 |
2004年 | 3篇 |
2003年 | 3篇 |
2002年 | 5篇 |
2001年 | 3篇 |
2000年 | 1篇 |
1999年 | 1篇 |
1997年 | 1篇 |
1995年 | 2篇 |
1991年 | 1篇 |
1990年 | 1篇 |
1989年 | 1篇 |
1987年 | 2篇 |
1984年 | 1篇 |
1983年 | 1篇 |
1981年 | 4篇 |
1978年 | 1篇 |
1977年 | 1篇 |
1975年 | 1篇 |
1972年 | 1篇 |
1970年 | 1篇 |
1969年 | 1篇 |
1968年 | 1篇 |
排序方式: 共有119条查询结果,搜索用时 15 毫秒
111.
112.
113.
114.
F. M. Flasar V. G. Kunde M. M. Abbas R. K. Achterberg P. Ade A. Barucci B. B’ezard G. L. Bjoraker J. C. Brasunas S. Calcutt R. Carlson C. J. C’esarsky B. J. Conrath A. Coradini R. Courtin A. Coustenis S. Edberg S. Edgington C. Ferrari T. Fouchet D. Gautier P. J. Gierasch K. Grossman P. Irwin D. E. Jennings E. Lellouch A. A. Mamoutkine A. Marten J. P. Meyer C. A. Nixon G. S. Orton T. C. Owen J. C. Pearl R. Prang’e F. Raulin P. L. Read P. N. Romani R. E. Samuelson M. E. Segura M. R. SHOWALTER A. A. Simon-Miller M. D. Smith J. R. Spencer L. J. Spilker F. W. Taylor 《Space Science Reviews》2004,115(1-4):169-297
The Composite Infrared Spectrometer (CIRS) is a remote-sensing Fourier Transform Spectrometer (FTS) on the Cassini orbiter that measures thermal radiation over two decades in wavenumber, from 10 to 1400 cm− 1 (1 mm to 7μ m), with a spectral resolution that can be set from 0.5 to 15.5 cm− 1. The far infrared portion of the spectrum (10–600 cm− 1) is measured with a polarizing interferometer having thermopile detectors with a common 4-mrad field of view (FOV). The middle infrared portion is measured with a traditional Michelson interferometer having two focal planes (600–1100 cm− 1, 1100–1400 cm− 1). Each focal plane is composed of a 1× 10 array of HgCdTe detectors, each detector having a 0.3-mrad FOV. CIRS observations will provide three-dimensional maps of temperature, gas composition, and aerosols/condensates of the atmospheres of Titan and Saturn with good vertical and horizontal resolution, from deep in their tropospheres to high in their mesospheres. CIRS’s ability to observe atmospheres in the limb-viewing mode (in addition to nadir) offers the opportunity to provide accurate and highly resolved vertical profiles of these atmospheric variables. The ability to observe with high-spectral resolution should facilitate the identification of new constituents. CIRS will also map the thermal and compositional properties of the surfaces of Saturn’s icy satellites. It will similarly map Saturn’s rings, characterizing their dynamical and spatial structure and constraining theories of their formation and evolution. The combination of broad spectral range, programmable spectral resolution, the small detector fields of view, and an orbiting spacecraft platform will allow CIRS to observe the Saturnian system in the thermal infrared at a level of detail not previously achieved.This revised version was published online in July 2005 with a corrected cover date. 相似文献
115.
Niemann H.B. Atreya S.K. Bauer S.J. Biemann K. Block B. Carignan G.R. Donahue T.M. Frost R.L. Gautier D. Haberman J.A. Harpold D. Hunten D.M. Israel G. Lunine J.I. Mauersberger K. Owen T.C. Raulin F. Richards J.E. Way S.H. 《Space Science Reviews》2002,104(1-4):553-591
The Gas Chromatograph Mass Spectrometer (GCMS) on the Huygens Probe will measure the chemical composition of Titan's atmosphere
from 170 km altitude (∼1 hPa) to the surface (∼1500 hPa) and determine the isotope ratios of the major gaseous constituents.
The GCMS will also analyze gas samples from the Aerosol Collector Pyrolyser (ACP) and may be able to investigate the composition
(including isotope ratios) of several candidate surface materials.
The GCMS is a quadrupole mass filter with a secondary electron multiplier detection system and a gas sampling system providing
continuous direct atmospheric composition measurements and batch sampling through three gas chromatographic (GC) columns.
The mass spectrometer employs five ion sources sequentially feeding the mass analyzer. Three ion sources serve as detectors
for the GC columns and two are dedicated to direct atmosphere sampling and ACP gas sampling respectively. The instrument is
also equipped with a chemical scrubber cell for noble gas analysis and a sample enrichment cell for selective measurement
of high boiling point carbon containing constituents. The mass range is 2 to 141 Dalton and the nominal detection threshold
is at a mixing ratio of 10− 8. The data rate available from the Probe system is 885 bit/s. The weight of the instrument is 17.3 kg and the energy required
for warm up and 150 minutes of operation is 110 Watt-hours.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
116.
Wiens Roger C. Neugebauer Marcia Reisenfeld Daniel B. Moses Ronald W. Nordholt Jane E. Burnett Donald S. 《Space Science Reviews》2003,105(3-4):601-626
The design and operation of the Genesis Solar-Wind Concentrator relies heavily on computer simulations. The computer model
is described here, as well as the solar wind conditions used as simulation inputs, including oxygen charge state, velocity,
thermal, and angular distributions. The simulation included effects such as ion backscattering losses, which also affect the
mass fractionation of the instrument. Calculations were performed for oxygen, the principal element of interest, as well as
for H and He. Ion fluences and oxygen mass fractionation are determined as a function of radius on the target. The results
were used to verify that the instrument was indeed meeting its requirements, and will help prepare for distribution of the
target samples upon return of the instrument to earth. The actual instrumental fractionation will be determined at that time
by comparing solar-wind neon isotope ratios measured in passive collectors with neon in the Concentrator target, and by using
a model similar to the one described here to extrapolate the instrumental fractionation to oxygen isotopes.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
117.
Nordholt Jane E. Wiens Roger C. Abeyta Rudy A. Baldonado Juan R. Burnett Donald S. Casey Patrick Everett Daniel T. Kroesche Joseph Lockhart Walter L. MacNeal Paul McComas David J. Mietz Donald E. Moses Ronald W. Neugebauer Marcia Poths Jane Reisenfeld Daniel B. Storms Steven A. Urdiales Carlos 《Space Science Reviews》2003,105(3-4):561-599
The primary goal of the Genesis Mission is to collect solar wind ions and, from their analysis, establish key isotopic ratios
that will help constrain models of solar nebula formation and evolution. The ratios of primary interest include 17O/16O and 18O/16O to ±0.1%, 15N/14N to ±1%, and the Li, Be, and B elemental and isotopic abundances. The required accuracies in N and O ratios cannot be achieved
without concentrating the solar wind and implanting it into low-background target materials that are returned to Earth for
analysis. The Genesis Concentrator is designed to concentrate the heavy ion flux from the solar wind by an average factor
of at least 20 and implant it into a target of ultra-pure, well-characterized materials. High-transparency grids held at high
voltages are used near the aperture to reject >90% of the protons, avoiding damage to the target. Another set of grids and
applied voltages are used to accelerate and focus the remaining ions to implant into the target. The design uses an energy-independent
parabolic ion mirror to focus ions onto a 6.2 cm diameter target of materials selected to contain levels of O and other elements
of interest established and documented to be below 10% of the levels expected from the concentrated solar wind. To optimize
the concentration of the ions, voltages are constantly adjusted based on real-time solar wind speed and temperature measurements
from the Genesis ion monitor. Construction of the Concentrator required new developments in ion optics; materials; and instrument
testing and handling.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
118.
Detection of Envisat RA2/ICE-1 retracked radar altimetry bias over the Amazon basin rivers using GPS
Stéphane Calmant Joecila Santos da Silva Daniel Medeiros Moreira Frédérique Seyler C.K. Shum Jean François Crétaux Germinal Gabalda 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Altimetry is now routinely used to monitor stage variations over rivers, including in the Amazon basin. It is desirable for hydrologic studies to be able to combine altimetry from different satellite missions with other hydrogeodesy datasets such as leveled gauges and watershed topography. One requirement is to accurately determine altimetry bias, which could be different for river studies from the altimetry calibrated for deep ocean or lake applications. In this study, we estimate the bias in the Envisat ranges derived from the ICE-1 waveform retracking, which are nowadays widely used in hydrologic applications. As a reference, we use an extensive dataset of altitudes of gauge zeros measured by GPS collocated at the gauges. The thirty-nine gauges are spread along the major tributaries of the Amazon basin. The methodology consists in jointly modeling the vertical bias and spatial and temporal slope variations between altimetry series located upstream and downstream of each gauge. The resulting bias of the Envisat ICE-1 retracked altimetry over rivers is 1.044 ± 0.212 m, revealing a significant departure from other Envisat calibrations or from the Jason-2 ICE-1 calibration. 相似文献
119.
The Juno Mission 总被引:1,自引:0,他引:1
S. J. Bolton J. Lunine D. Stevenson J. E. P. Connerney S. Levin T. C. Owen F. Bagenal D. Gautier A. P. Ingersoll G. S. Orton T. Guillot W. Hubbard J. Bloxham A. Coradini S. K. Stephens P. Mokashi R. Thorne R. Thorpe 《Space Science Reviews》2017,211(1-4):5-95
The selection of the Discovery Program InSight landing site took over four years from initial identification of possible areas that met engineering constraints, to downselection via targeted data from orbiters (especially Mars Reconnaissance Orbiter (MRO) Context Camera (CTX) and High-Resolution Imaging Science Experiment (HiRISE) images), to selection and certification via sophisticated entry, descent and landing (EDL) simulations. Constraints on elevation (\({\leq}{-}2.5\ \mbox{km}\) for sufficient atmosphere to slow the lander), latitude (initially 15°S–5°N and later 3°N–5°N for solar power and thermal management of the spacecraft), ellipse size (130 km by 27 km from ballistic entry and descent), and a load bearing surface without thick deposits of dust, severely limited acceptable areas to western Elysium Planitia. Within this area, 16 prospective ellipses were identified, which lie ~600 km north of the Mars Science Laboratory (MSL) rover. Mapping of terrains in rapidly acquired CTX images identified especially benign smooth terrain and led to the downselection to four northern ellipses. Acquisition of nearly continuous HiRISE, additional Thermal Emission Imaging System (THEMIS), and High Resolution Stereo Camera (HRSC) images, along with radar data confirmed that ellipse E9 met all landing site constraints: with slopes <15° at 84 m and 2 m length scales for radar tracking and touchdown stability, low rock abundance (<10 %) to avoid impact and spacecraft tip over, instrument deployment constraints, which included identical slope and rock abundance constraints, a radar reflective and load bearing surface, and a fragmented regolith ~5 m thick for full penetration of the heat flow probe. Unlike other Mars landers, science objectives did not directly influence landing site selection. 相似文献