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452.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(10):2290-2302
The HP3 instrument measures the thermal flux through the Martian crust using a penetration probe. Launched on the InSight mission in 2018, HP3 was deployed for penetration activities in the beginning of 2019. During initial operation, the instrument is vulnerable to slip, due to a combination of low system mass (3.3 kg on Earth), shocks delivered by the penetration probe’s action, and the possibility of an inclined attitude on the surface. An uncontrolled position change of the instrument on the surface can reduce the scientific output and even lead to a loss of the experiment if the probe’s supporting structure moves laterally. Naturally, the design of the feet has major impact on the total amount of slippage. A new design for the feet with a high slippage resistance capability at a low level of complexity and mass was developed for this instrument’s supporting structure. The design provides sufficient slippage resistance while fulfilling the challenging set of requirements for a Mars surface mission. The design was verified by test campaigns which emulate launch environments and operational behavior on Mars. This paper gives a detailed overview of the HP3 instrument itself, the relevant requirements, the complex different test campaigns and the final flight design. 相似文献
453.
S. Dell’Agnello G.O. Delle Monache D.G. Currie R. Vittori C. Cantone M. Garattini A. Boni M. Martini C. Lops N. Intaglietta R. Tauraso D.A. Arnold M.R. Pearlman G. Bianco S. Zerbini M. Maiello S. Berardi L. Porcelli C.O. Alley J.F. McGarry C. Sciarretta V. Luceri T.W. Zagwodzki 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
We built a new experimental apparatus (the “Satellite/lunar laser ranging Characterization Facility”, SCF) and created a new test procedure (the SCF-Test) to characterize and model the detailed thermal behavior and the optical performance of cube corner laser retroreflectors in space for industrial and scientific applications. The primary goal of these innovative tools is to provide critical design and diagnostic capabilities for Satellites Laser Ranging (SLR) to Galileo and other GNSS (Global Navigation Satellite System) constellations. The capability will allow us to optimize the design of GNSS laser retroreflector payloads to maximize ranging efficiency, to improve signal-to-noise conditions in daylight and to provide pre-launch validation of retroreflector performance under laboratory-simulated space conditions. Implementation of new retroreflector designs being studied will help to improve GNSS orbits, which will then increase the accuracy, stability, and distribution of the International Terrestrial Reference Frame (ITRF), to provide better definition of the geocenter (origin) and the scale (length unit). 相似文献
454.
Sensitivity analyses of satellite propulsion components with their thermal modelling 总被引:1,自引:0,他引:1
Cho Young Han Jae Ho You Kyun Ho Lee Hui Kyung Kim Sung Nam Lee 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
Performing the sensitivity analyses of the contact conduction and the position of thermostat on the basis of the thermal model established, the study of thermal design is accomplished for the preparation of possible mechanical interface change of the satellite propulsion system depending on the satellite system design. A relatively simple thermal model is taken into consideration for the convenience of the analysis. A variety of the spacecraft bus voltages and the contact resistances are examined as well as the position of thermostat on propulsion components. As a consequence, even though the mechanical interface condition is changed on the same module, the successful thermal design could be achieved if we design the heater to have sufficiently large power with reference to the heritage value of contact resistance. Besides the reasonable performance on the thermal control is assured with the thermostat location errors, if the uncertainty in the position of thermostat is not quite large when assembling tank module. 相似文献
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直接推力控制可以有效改善推力控制的品质,针对航空发动机直接推力控制问题,进行了模型预测控制(Model Predictive Control, MPC)研究。为了提升航空发动机推力控制的精度,提出了基于复合推进系统动态模型-状态变量模型(Compact Propulsion System Dynamic Model-State Variable Model-State Variable Model, CPSDM-SVM)的航空发动机直接推力预测控制方法。CPSDM实时估计出不可测参数(推力、喘振裕度等)的基准值,SVM则根据未来输入实时预测发动机未来响应。由于CPSDM将发动机分为进气道、核心机、喷管、喘振裕度、推力等进行建模,在兼顾精度的同时,提高机载模型的实时性。CPSDM-SVM作为MPC算法中的预测模型,具有较高的精度和实时性。仿真结果表明,在与基于分段线化模型的传统模型预测控制方法实时性基本相同的情况下,所提出方法控制效果有明显的提升,调节时间减小了1.17s。所提出方法稳态控制精度为0.08%,传统方法稳态精度为2.58%。因此,所提出方法在保证实时性的条件下,提升了控制精度和控制效果。 相似文献
458.
Laser melting deposition was carried out to deposit a 1Cr12Ni2WMoVNb steel bar on a wrought bar of same material. Room-temperature tensile properties of the hybrid fabricated 1Cr12Ni2WMoVNb steel sample were evaluated, and microstructure, fracture surface morphology, and hardness profile were analyzed by an optical microscope (OM), a scanning electron microscope (SEM), and a hardness tester. Results show that the hybrid fabricated 1Cr12Ni2WMoVNb steel sample consists of laser deposited zone, wrought substrate zone, and heat affected zone (HAZ) of the wrought substrate. The laser deposited zone has coarse columnar prior austenite grains and fine well-aligned dendritic structure, while the HAZ of the wrought substrate has equiaxed prior austenite grains which are notably finer than those in the wrought substrate zone. Besides, austenitic transformation mechanism of the HAZ of the wrought substrate is different from that of the laser deposited zone during the reheating period of the laser deposition, which determines the different prior austenite grain morphologies of the two zones. Microhardness values of both the laser deposited zone and the HAZ of the wrought substrate are higher than that of the wrought substrate zone. Tensile properties of the hybrid fabricated 1Cr12Ni2WMoVNb steel sample are comparable to those of the wrought bar, and fracture occurs in the wrought substrate zone during the tensile test. 相似文献
459.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013,52(2):262-271
In this paper we review the lunar laser ranging conducted by the laser altimeter (LALT) on board the KAGUYA lunar explorer (2007–2009). Five aspects of LALT measurements are described: (1) General operational history, (2) Laser shot and data statistics, (3) Revisions to LALT topographic data, (4) Variations in laser output energy, and (5) Peak height analysis of laser echo pulses. LALT was able to range to the lunar surface despite some troubles with respect to laser output energy in the middle of the KAGUYA mission. The time series topographic data set was revised (Ver. 2) by incorporating new lunar gravity model based on KAGUYA and other historical lunar satellite’s orbit data, along with other improvements, for example by incorporating the accurate position of the laser collimator on board the KAGUYA; however, more than half of the acquired range data could not be converted properly due to problems with orbit accuracy during the extended phase of the mission. The spherical harmonic coefficients and the basic lunar figure parameters derived from LALT_LGT_TS agree very well with LRO-LOLA and the Chang’E-1 LAM model. It is possible that partial failure to the laser diode was responsible for the gradual degradation of laser power (0.835 mJ per million shots) and the rapid decrease that occurred over April 9–14, 2008. The laser power also proved to be extremely sensitive to the temperature of the laser oscillator. The peak height ratio – that is peak height telemetry data divided by calculated ratio – is about 19% on average using the mean slope and albedo data from LALT and Spectral Profiler on KAGUYA space craft, respectively, which suggests the performance of peak height measurement is more than 1/5 for more than 70 km altitude, if compared with calculated one. The peak height ratio may be better if we take the effect of small scale topography within a footprint into account. 相似文献
460.