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141.
The techniques of forming the mobile sliding manifolds and vector controls, which bring these systems into the sliding modes under continuous action of uncertain factors, namely limited disturbances and total errors in measurements, are developed for dynamic systems with discontinuous control. The techniques are applicable for effective control of complex aerospace objects. 相似文献
142.
V. A. Kudinov A. V. Eremin A. E. Kuznetsova E. V. Stefanyuk 《Russian Aeronautics (Iz VUZ)》2014,57(1):37-44
An exact analytical solution of the thermoelasticity problem is presented for a multilayer shallow cylinder with physical properties of the medium that are constant in the limits of each layer. The effect of thermal shock of different intensity as well as the penetration depth of thermal disturbance on the distribution of radial and circumferential thermal stresses has been studied as applied to the one- and two-layer cylinder. It has been shown that the circumferential compressive stresses appear on the external surface of the cylinder under thermal shock while the tensile stresses appear on the internal surface. 相似文献
143.
A. A. Abdyushev 《Russian Aeronautics (Iz VUZ)》2013,56(2):117-125
The equilibrium between the rods and panels in the ribbed shells is considered based on the total system of structural mechanics equations as applied to a discrete model. Also shown is an approach to solving the problems that permits the stiffness matrix of shear panels to be obtained with regard for the equilibrium along the boundary with rods. The connection with the standard hybrid method of constructing stiffness matrices is indicated. The solutions for separate elements and examples illustrating the approach being proposed are presented. 相似文献
144.
A problem of transverse bending of elastic isotropic parallelogram plates under the action of uniformly distributed load is considered. The plate sides are either pivoted or rigidly restrained. To determine the value of maximum plate deflection, it is proposed that an interpolation technique with respect to form factor be used; and as a geometrical argument, an inner-outer conformal radius ratio can be applied instead of the form factor. 相似文献
145.
The paper presents the results of calculating nonstatitionary heat exchange between a heattransfer agent (water) and a gadolinium working element of the thermomagnetic engine with the use of ANSYS 13.0 certified software. Recommendations for designing the thermomagnetic engine working elements are given based on the analysis of calculation results. 相似文献
146.
In this paper, we consider some typical values of motion parameters in exceptional situations when approaching to the helicopter critical flight regimes and present a technique for constructing the partial and integral informative functions of hazards at current flight regimes. Also described are the possibilities of their use for solving the problems of warning, informative crew support, and synthesizing the control algorithms to remove helicopter from the exceptional situation occurred. 相似文献
147.
V. A. Trushin 《Russian Aeronautics (Iz VUZ)》2013,56(4):372-378
The finite-difference method acceptable for on-board computers is applied to analyze the thermo-stressed state for the thermal-barrier coating of a perforated turbine blade and its wall at transient and stationary conditions of air-breathing jet engine operation during a flight. 相似文献
148.
介绍一种新型的、具有最小喉道面积的三维高超声速进气道(称之为收敛形进气道)的数值和实验研究结果.表明使用这种形式的进气道,在整个飞行速度范围内可以降低阻力和高超声速发动机表面的热防护要求,通过降低外压缩表面的倾斜度和减少进气道及燃烧室壁的面积就可以做到这一点.在采用低维次流动的气体动力设计方法的基础上设计成这种形式的进气道.计算是在无粘气体模型构架内用有限体积法进行的.同时用边界层方程计算出计及粘性的气流特性和进气道特性.数值算法是通过收敛形进气道的有限宽楔形外压缩表面的计算和实验数据来验证的.进行实验研究的马赫数M=2~10.7,基于模型进气道高度的雷诺数Re=(1~5)×106. 数值计算与实验结果一致性很好.这些结果也和通常的二维进气道的数据作了比较. 相似文献
149.
150.
M.D. Ngobeni M.S. Potgieter 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
Observations of galactic cosmic rays (GCRs) from the two Voyager spacecraft inside the heliosheath indicate significant differences between them, suggesting that in addition to a possible global asymmetry in the north–south dimensions (meridional plane) of the heliosphere, it is also possible that different modulation (turbulence) conditions could exist between the two hemispheres of the heliosphere. We focus on illustrating the effects on GCR Carbon of asymmetrical modulation conditions combined with a heliosheath thickness that has a significant dependence on heliolatitude. To reflect different modulation conditions between the two heliospheric hemispheres in our numerical model, the enhancement of both polar and radial perpendicular diffusion off the ecliptic plane is assumed to differ from heliographic pole to pole. The computed radial GCR intensities at polar angles of 55° (approximating the Voyager 1 direction) and 125° (approximating the Voyager 2 direction) are compared at different energies and for both particle drift cycles. This is done in the context of illustrating how different values of the enhancement of both polar and radial perpendicular diffusion between the two hemispheres contribute to causing differences in radial intensities during solar minimum and moderate maximum conditions. We find that in the A > 0 cycle these differences between 55° and 125° change both quantitatively and qualitatively for the assumed asymmetrical modulation condition as reflected by polar diffusion, while in the A < 0 cycle, minute quantitative differences are obtained. However, when both polar and radial perpendicular diffusion have significant latitude dependences, major differences in radial intensities between the two polar angles are obtained in both polarity cycles. Furthermore, significant differences in radial intensity gradients obtained in the heliosheath at lower energies may suggest that the solar wind turbulence at and beyond the solar wind termination shock must have a larger latitudinal dependence. 相似文献