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131.
132.
为了研究空间微小碎片碰撞对航天器的影响,国内外研制了各种类型的微小碎片加速器。文章简要介绍了一种很有前景的静电式微小碎片加速器及其关键部件的工作原理、结构特点及适用范围等。 相似文献
133.
The chemical composition of comet nuclei derived from current data on interstellar dust ingredients and comet dust and coma
molecules are shown to be substantially consistent with each other in both refractory and volatile components. When limited
by relative cosmic abundances the water in comet nuclei is constrained to be close to 30% by mass and the refractory to volatile
ratio is close to 1:1. The morphological structure of comet nuclei, as deduced from comet dust infrared continuum and spectral
emission properties, is described by a fluffy (porous) aggregate of tenth micron silicate core-organic refractory mantle particle
on which outer mantles of predominantly H2O ices contain embedded carbonaceous and polycyclic aromatic hydrocarbon (PAH) type particles of size in the of 1 - 10nm range.
This revised version was published online in June 2006 with corrections to the Cover Date. 相似文献
134.
Haiyang Li Jingyang Li Fanghua Jiang 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(1):154-166
Tumbling debris has become a great threat to orbit activities. Contactless interaction is a novel concept for active debris removal, through which the tumbling debris no longer rotates freely but is under control. The contactless interaction method aims to de-tumble the debris and then maintain desired relative states between the spacecraft and debris. The spacecraft is simultaneously stabilized through three-axis attitude control, which makes the de-tumbling and capture operation much safer, more effective and accurate. The dynamics and control for the contactless interaction have been little studied in the past years. This paper considers a generic dynamics and control problem for contactless interaction between a spacecraft and debris. A translational and rotational dynamics model of contactless interaction is proposed and the 6-DOF equations are established. The contactless interaction control law is designed with the backstepping method, and the spacecraft three-axis control law is designed with the PD control. Simulation results show that the angular momentum is transferred from the debris to the spacecraft and the debris is thus de-tumbled. The desired relative states are achieved efficiently. Significantly, the spacecraft and debris no longer rotate in the inertial frame and, hence, the safety and accuracy for capture operation are guaranteed. 相似文献
135.
The milling stability of thin-walled components is an important issue in the aviation manufacturing industry,which greatly limits the removal rate of a workpiece.However,for a thin-walled workpiece,the dynamic characteristics vary at different positions.In addition,the removed part also has influence on determining the modal parameters of the workpiece.Thus,the milling stability is also time-variant.In this work,in order to investigate the time variation of a workpiece's dynamic characteristics,a new computational model is firstly derived by dividing the workpiece into a removed part and a remaining part with the Ritz method.Then,an updated frequency response function is obtained by Lagrange's equation and the corresponding modal parameters are extracted.Finally,multi-mode stability lobes are plotted by the different quadrature method and its accuracy is verified by experiments.The proposed method improves the computational efficiency to predict the time-varying characteristics of a thin-walled workpiece. 相似文献
136.
为了研发具有自主知识产权的气源起动装备,立足于大型飞机较高压力、超大流量的特殊气源起动保障需求,设计了以双级无油螺杆压缩为核心技术的供气流程,对其中涉及的级间压力、散热量、除水量等关键参数进行了分析与计算,为解决超大流量气源的二次升压、风冷散热、高温除水等核心技术难题奠定了基础。 相似文献
137.
James Mason Jan Stupl William Marshall Creon Levit 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
We focus on preventing collisions between debris and debris, for which there is no current, effective mitigation strategy. We investigate the feasibility of using a medium-powered (5 kW) ground-based laser combined with a ground-based telescope to prevent collisions between debris objects in low-Earth orbit (LEO). The scheme utilizes photon pressure alone as a means to perturb the orbit of a debris object. Applied over multiple engagements, this alters the debris orbit sufficiently to reduce the risk of an upcoming conjunction. We employ standard assumptions for atmospheric conditions and the resulting beam propagation. Using case studies designed to represent the properties (e.g. area and mass) of the current debris population, we show that one could significantly reduce the risk of nearly half of all catastrophic collisions involving debris using only one such laser/telescope facility. We speculate on whether this could mitigate the debris fragmentation rate such that it falls below the natural debris re-entry rate due to atmospheric drag, and thus whether continuous long-term operation could entirely mitigate the Kessler syndrome in LEO, without need for relatively expensive active debris removal. 相似文献
138.
ISO performed a large variety of observing programmes on comets, asteroids and zodiacal light – covering about 1% of the archived
observations – with a surprisingly rewarding scientific return. Outstanding results were related to the exceptionally bright
comet Hale–Bopp and to ISO's capability to study in detail the water spectrum in a direct way. But many other results were
broadly recognised: Discovery of new molecules in comets, the studies of crystalline silicates, the work on asteroid surface
mineralogy, results from thermophysical studies of asteroids, a new determination of the asteroid number density in the main-belt
and last but not least, the investigations on the spatial and spectral features of the zodiacal light. 相似文献
139.
Harald Krüger Markus Landgraf Nicolas Altobelli Eberhard Grün 《Space Science Reviews》2007,130(1-4):401-408
The Ulysses spacecraft has been orbiting the Sun on a highly inclined ellipse almost perpendicular to the ecliptic plane (inclination
79°, perihelion distance 1.3 AU, aphelion distance 5.4 AU) since it encountered Jupiter in 1992. The in situ dust detector
on board continuously measured interstellar dust grains with masses up to 10−13 kg, penetrating deep into the solar system. The flow direction is close to the mean apex of the Sun’s motion through the
solar system and the grains act as tracers of the physical conditions in the local interstellar cloud (LIC). While Ulysses
monitored the interstellar dust stream at high ecliptic latitudes between 3 and 5 AU, interstellar impactors were also measured
with the in situ dust detectors on board Cassini, Galileo and Helios, covering a heliocentric distance range between 0.3 and
3 AU in the ecliptic plane. The interstellar dust stream in the inner solar system is altered by the solar radiation pressure
force, gravitational focussing and interaction of charged grains with the time varying interplanetary magnetic field. We review
the results from in situ interstellar dust measurements in the solar system and present Ulysses’ latest interstellar dust
data. These data indicate a 30° shift in the impact direction of interstellar grains w.r.t. the interstellar helium flow direction,
the reason of which is presently unknown. 相似文献
140.
Johannes Mathies Steffen Mauceri Lukas Pfeiffer Marco Vietze Hans-Peter Roeser Felix BoehringerMichael Lengowski 《Acta Astronautica》2014
SSETO is the result of a phase-A study in context of the small satellite program of the University of Stuttgart that demonstrates the capability of a university institute to build a small satellite with a budget of 5 million Euro. The satellite will be capable of observing exoplanets in a Neptune–Earth scale and obtaining data of interstellar dust. Due to a system failure of NASA?s Kepler mission, there is currently (October 2013) a lack of satellites searching for exoplanets. This paper details the design of subsystems and payload, as well as the required test tasks in accordance with the mission profile at a conceptional level. The costs for standard spacecraft testing and integration tasks are included, but not those of launch, ground support, operations and engineer working hours. 相似文献