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41.
Jeng-Shing Chern Ching-Yew Yang Nguyen X. Vinh John M. Hanson 《Acta Astronautica》1985,12(10):819-829
With increasing frequency in shuttle operation, it is of interest to have more than one or two landing fields within the boundary of the reachable area of the reentry vehicle. This boundary, called the footprint, depends on the aerodynamic characteristics of the vehicle and is severely restricted by the deceleration and heating constraints imposed upon the atmospheric reentry trajectory. This paper gives a general assessment of the footprint as a function of various deceleration and heating constraints. The difficulties in the computation of the three-dimensional reentry trajectories with optimal modulation in both the angle-of-attack and the bank angle are alleviated by the following devices: (a) nondimensionalizing of the equations of motion and use of the density as the altitude variable; (b) use of the classical integrals of the motion; (c) transformation of the adjoint variables into physical variables; and (d) spherical rotation of the coordinates. 相似文献
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44.
The US spent all of the funds originally estimated for the initial development of its orbital space station without producing any significant amount of flight hardware. This article shows how a project with large design costs and significant “non-prime” outlays can quickly deplete program funds. The authors recount the way in which budgetary politics, congressional micro-management, and technological risk conspired to produce this result. 相似文献
45.
James M. Russell Ellis E. Remsberg John C. Gille Larry L. Gordley 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》1981,1(4):271-277
The Limb Infrared Monitor of the Stratosphere (LIMS) experiment is a limb scanning infrared sounder designed to measure vertical temperature profiles and the concentrations of key chemical compounds which are important in the stratospheric ozone-nitrogen photochemistry. This paper describes results from the O3 and HNO3 channels with emphasis on validation of the data. Similar discussions of results from the other channels are presented in two companion papers published in these proceedings. 相似文献
46.
Nielson John T. Swearingen Gary W. Witsmeer A. J. 《Aerospace and Electronic Systems Magazine, IEEE》1986,1(3):20-26
The Global Positioning System is an extremely accurate satellite-based navigation system which, after its completion in 1989, will provide users worldwide, 24 hour. all weather coverage. A joint research project among Boeing, Rockwell-Collins, and Northrop has been completed in which a GPS receiver was integrated with a low-cost strap-down inertial navigation system and a flight computer. A Kalman filter in the latter allows in-fight alignment and calibration of the INS. In addition, feedback from the INS to the GPS receiver improves the system's ability to reacquire satellite signals after outages. The resulting system combines the accuracy of GPS with the jamming immunity and autonomy of inertial navigation. System tests were conducted in which a Boeing owned T-33 jet aircraft was flown through known test pattern to align and calibrate the INS. Earlier tests, including tests against an airborne jammer, were conducted in a modified passenger bus. 相似文献
47.
John F. Kerridge 《Space Science Reviews》1991,56(1-2):177-184
Carbon isotope ratios have been measured for CN in the coma of comet Halley and for several CHON particles emitted by Halley. Of these, only the CHON-particle data may be reasonably related to organic matter in the cometary nucleus, but the true range of 13C/12C values in those particles is quite uncertain. The D/H ratio in H2O in the Halley coma resembles that in Titan/Uranus. The next decade should substantially improve our understanding of the distribution of C, H, N, and O isotopes in cometary organics. The isotopic composition of meteoritic organic matter is better understood and can serve as a useful analog for the cometary case. 相似文献
48.
Gordon Pike 《Space Policy》1991,7(2)
This article describes aspects of the Chinese space programme of interest to potential users of Chinese commercial launch services. A brief history is included along with a review of the current licensing requirements of the US government. The rationale behind Aussat's choice of the Long March launch vehicle is presented as well as a brief comment on the likely future for Chinese launch services in the West. 相似文献
49.
Radar Imaging of Mercury 总被引:1,自引:0,他引:1
John K. Harmon 《Space Science Reviews》2007,132(2-4):307-349
Earth-based radar has been one of the few, and one of the most important, sources of new information about Mercury during
the three decades since the Mariner 10 encounters. The emphasis during the past 15 years has been on full-disk, dual-polarization
imaging of the planet, an effort that has been facilitated by the development of novel radar techniques and by improvements
in radar systems. Probably the most important result of the imaging work has been the discovery and mapping of radar-bright
features at the poles. The radar scattering properties of these features, and their confinement to permanently shaded crater
floors, is consistent with volume backscatter from a low-loss volatile such as clean water ice. Questions remain, however,
regarding the source and long-term stability of the putative ice, which underscores the need for independent confirmation
by other observational methods. Radar images of the non-polar regions have also revealed a plethora of bright features, most
of which are associated with fresh craters and their ejecta. Several very large impact features, with rays and other bright
ejecta spreading over distances of 1,000 km or more, have been traced to source craters with diameters of 80–125 km. Among
these large rayed features are some whose relative faintness suggests that they are being observed in an intermediate stage
of degradation. Less extended ray/ejecta features have been found for some of the freshest medium-size craters such as Kuiper
and Degas. Much more common are smaller (<40 km diameter) fresh craters showing bright rim-rings but little or no ray structure.
These smaller radar-bright craters are particularly common over the H-7 quadrangle. Diffuse areas of enhanced depolarized
brightness have been found in the smooth plains, including the circum-Caloris planitiae and Tolstoj Basin. This is an interesting
finding, as it is the reverse of the albedo contrast seen between the radar-dark maria and the radar-bright cratered highlands
on the Moon. 相似文献
50.
In order to verify that the International Space Station (ISS) payload facility racks do not disturb the microgravity environment of neighboring facility racks and that the facility science operations are not compromised, a testing and analytical verification process must be followed. Currently no facility racks have taken this process from start to finish. The authors are participants in implementing this process for the NASA Glenn Research Center (GRC) Fluids and Combustion Facility (FCF). To address the testing part of the verification process, the Microgravity Emissions Laboratory (MEL) was developed at GRC. The MEL is a 6 degree of freedom inertial measurement system capable of characterizing inertial response forces (emissions) of components, sub-rack payloads, or rack-level payloads down to 10(-7) g's. The inertial force output data, generated from the steady state or transient operations of the test articles, are utilized in analytical simulations to predict the on-orbit vibratory environment at specific science or rack interface locations. Once the facility payload rack and disturbers are properly modeled an assessment can be made as to whether required microgravity levels are achieved. The modeling is utilized to develop microgravity predictions which lead to the development of microgravity sensitive ISS experiment operations once on-orbit. The on-orbit measurements will be verified by use of the NASA GRC Space Acceleration Measurement System (SAMS). The major topics to be addressed in this paper are: (1) Microgravity Requirements, (2) Microgravity Disturbers, (3) MEL Testing, (4) Disturbance Control, (5) Microgravity Control Process, and (6) On-Orbit Predictions and Verification. 相似文献