全文获取类型
收费全文 | 8335篇 |
免费 | 18篇 |
国内免费 | 23篇 |
专业分类
航空 | 3719篇 |
航天技术 | 2852篇 |
综合类 | 31篇 |
航天 | 1774篇 |
出版年
2021年 | 89篇 |
2019年 | 50篇 |
2018年 | 252篇 |
2017年 | 165篇 |
2016年 | 150篇 |
2015年 | 62篇 |
2014年 | 218篇 |
2013年 | 274篇 |
2012年 | 255篇 |
2011年 | 384篇 |
2010年 | 279篇 |
2009年 | 409篇 |
2008年 | 433篇 |
2007年 | 276篇 |
2006年 | 188篇 |
2005年 | 233篇 |
2004年 | 219篇 |
2003年 | 258篇 |
2002年 | 184篇 |
2001年 | 272篇 |
2000年 | 142篇 |
1999年 | 181篇 |
1998年 | 220篇 |
1997年 | 136篇 |
1996年 | 188篇 |
1995年 | 243篇 |
1994年 | 222篇 |
1993年 | 129篇 |
1992年 | 170篇 |
1991年 | 54篇 |
1990年 | 61篇 |
1989年 | 159篇 |
1988年 | 65篇 |
1987年 | 66篇 |
1986年 | 75篇 |
1985年 | 221篇 |
1984年 | 177篇 |
1983年 | 135篇 |
1982年 | 141篇 |
1981年 | 247篇 |
1980年 | 65篇 |
1979年 | 55篇 |
1978年 | 58篇 |
1977年 | 51篇 |
1975年 | 58篇 |
1974年 | 46篇 |
1973年 | 37篇 |
1972年 | 46篇 |
1971年 | 44篇 |
1970年 | 42篇 |
排序方式: 共有8376条查询结果,搜索用时 15 毫秒
91.
The basic steps of an algorithm are given for calculating the parameters of the limiting state of a helicopter main rotor
blade. To estimate the static strength, a technique of elastic constants variation is used; it is based on the limit equilibrium
theory and enables us to obtain the upper and lower bounds for the critical load simultaneously. An iterative technique is
proposed to determine the lower bound of the allowable load on the root section of the composite blade depending on the azimuthal
angle of its turn in the helicopter hovering mode. 相似文献
92.
A technique of analyzing the flutter initiation in flat plate compressor cascades was developed. The viscous and inviscid
flow study was carried out using the COBRA solver based on the modified implicit Godunov method and unsteady implicit method
updated for using. The flutter conditions were revealed and the effect of taking into account viscosity, angles of attack
and time steps was investigated. 相似文献
93.
V. A. Futin 《Russian Aeronautics (Iz VUZ)》2011,54(2):165-169
The influence of the clearance between the case and blade ends of the semi-open impeller on the centrifugal stage characteristics
is considered using the experimental data and numerical calculation results. 相似文献
94.
The influence of geometry and operating conditions of the centrifugal compressor stage on the radial gas force is determined
on the basis of the theoretical method and calculation program using experimental boundary conditions. 相似文献
95.
M. V. Usanin A. A. Siner A. M. Sipatov L. Yu. Gomzikov V. G. Avgustinovich 《Russian Aeronautics (Iz VUZ)》2011,54(1):34-42
The application of the low dissipative high-order accurate scheme for numerical solution of the Euler and Navier-Stokes equations
in the two-dimensional statement is considered. The scheme of calculating space derivatives is the seven-point central-difference
approximation of the fourth order with the coefficients optimized to reduce the dispersion errors. The optimized six-step
Runge-Kutta method is used for evaluating the time derivatives. By means of filtration, spurious pulsations are suppressed
and shocks are processed. The results of verifying the calculation scheme realized on the stationary problem of flow around
the model turbine blades are presented. 相似文献
96.
S. V. Russkikh 《Russian Aeronautics (Iz VUZ)》2014,57(1):107-110
Transverse nonstationary vibrations of a guide beam having the initial flexure are considered. An absolutely rigid missile moves under the propulsive force along this guide beam on two sliding supports. The beam displacements introduced by its vibrations are presented as an expansion with respect to the given functions according to the Ritz method. The equations of nonstationary vibration of the beam with the missile moving along it are obtained in the generalized coordinates, the expansion coefficients being chosen as them. The example is presented. Also studied is the effect of different beam and missile parameters on the beam displacement and transverse and angular velocity of the missile. 相似文献
97.
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
98.
A problem of modeling the incompressible viscous flow between two disks taking into account the rotation of one of them is
considered. We study the effect of the disk angular velocity (flow regimes) in the interdisk spacing, finiteness (infiniteness)
of disk radiuses, calculation region configuration as well as distances between disks on the flow characteristics, particularly,
on the resistance moment coefficient. Numerical simulation is performed with the aid of Maple and ANSYS Fluent software. 相似文献
99.
N. D. Akhmetov M. M. Gimadeev V. N. Drulis V. A. Krivosheev T. V. Rzaeva 《Russian Aeronautics (Iz VUZ)》2011,54(1):108-113
A technique for calculating the energy parameters of shock waves at electrical discharge in water is presented for the transition
region of discharge channel expansion using as the base the predetermined characteristics of discharge circuit. The technique
is based on the solution of energy transport equation that is similar in form to that of radiative transfer. The validity
of the presented approach was experimentally verified. 相似文献
100.
Systems for the indication and display of secondary information in avionics and autobasing complexes
A. A. Bagdasarov R. V. Anitropov O. V. Bagdasarova I. L. Livshits 《Russian Aeronautics (Iz VUZ)》2011,54(2):185-191
We consider the peculiarities of application for the cabin indicating systems of secondary information display, formulate
and systematize the compositional and technical requirements for display systems and their elements. The tendencies and lines
in the development of head-up displays for avionics and autobasing complexes were determined. The technique of calculating
optics of such display systems with the use of electronic distortion compensation is presented. 相似文献