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假设纤维方向角沿层合板的长度方向线性变化,研究了变角度纤维复合材料层合斜板的颤振.通过坐标变换将斜板变换为正方形板,采用层合板表面连续变化的速度环量来模拟空气对其的作用,速度环量分布利用Cauchy积分公式计算.建立了系统的Lagrange方程并采用Ritz法得到了层合板的自振频率和颤振/不稳定性分离临界速度.通过数值算例验证了本文模型和方法的正确性和收敛性,分析了各个铺层内纤维方向角的变化对自振频率和颤振/不稳定性分离临界速度的影响.研究结果表明,通过纤维的变角度铺设,可有效地提高层合板的基频和颤振/不稳定性分离临界速度.经合理设计的变角度复合材料层合板具有抑制颤振的作用. 相似文献
4.
The generalized aerodynamic force (GAF) matrix is derived for the Unsteady Vortex Lattice Method (UVLM) without the assumption of out-of-plane dynamics. As a result, the approach naturally includes in-plane motion and forces unlike the doublet lattice method (DLM). The derived UVLM GAF is therefore applicable to industry-standard techniques for aeroelastic stability analyses, such as the p–k method. In this work, the fluid–structure interpolation is performed with radial basis functions for surface interpolation. The generalized aerodynamic forces computed with the UVLM are verified against the DLM from NASTRAN on a simple flat plate configuration. The ability of the UVLM to include steady loads is verified with a T-tail flutter case and the results confirm the importance of including steady loads for T-tail flutter analysis. The modal frequency domain VLM therefore provides the same level of efficiency and accuracy than the DLM, but without the restrictions and with the ability to handle complex geometries. It is therefore a viable replacement to the DLM. 相似文献
5.
P.M. Ligrani R. Van Den Braembussche M. Roustan 《International Journal of Heat and Fluid Flow》1983,4(2):103-106
Results from an experimental study of flow behaviour at the inlet of a vaneless diffuser of a centrifugal compressor are presented. Measurements from a crossed hot-wire probe are given for operating points having inlet flow coefficients ranging from 0.006 to 0.019 at different Reynolds numbers. Instantaneous, time-averaged, and phase-averaged absolute velocity and flow angle at the diffuser inlet are deduced from the hot-wire signals after correction for mean density variations. These results show how flow behaviour varies in stable, rotating stall and surge regimes of compressor operation 相似文献
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等速上仰翼型动态失速现象研究 总被引:9,自引:0,他引:9
翼型大迎角绕流的静态失速将造成升力突降和气动性能急剧恶化,但利用非定常运动所产生
的动态失速效应,可以大大地延缓气流分离和失速现象的发生. 采用Rogers发
展的双时间步Roe格式,求解拟压缩性修正不可压N-S方程. 数值模拟了低雷诺数
($Re=4.8 \times 10^{4}$)条件下NACA0015翼型作等速上仰($\alpha
=0^{\circ} \sim 60^{\circ}$)的动态失速过程,同Walker的试验结果比
较,验证了计算结果的正确性. 研究了该过程中主涡、二次涡和三次涡的发展,升
力系数随攻角变化,以及不同上仰速度对动态失速效应所造成的影响. 相似文献
7.
本文对动失速型非定常分离涡结构的控制方法,在低速风洞中应用相平均测压技术进行了实验研究。在二元平板模型中部安装一作俯仰振荡的扰流板产生动失速型分离涡,在其上游安装另一用作控制的小扰流板。实验结果表明,应用前置的振荡小扰流板可影响并改变动失速分离涡的强度和对流特性。在最有利的控制相位下,涡吸力峰可降低48%,涡对流时间可以推迟0.19周期。对于间歇式振荡扰流板,采用相位提前控制方式比相位滞后控制方式更有效。 相似文献
8.
Slobodan R. Sipcic 《Nonlinear dynamics》1990,1(3):243-264
The influence of maneuvering on the chaotic response of a fluttering buckled plate on an aircraft has been studied. The governing equations, derived using Lagrangian mechanics, include geometric non-linearities associated with the occurrence of tensile stresses, as well as coupling between the angular velocity of the maneuver and the elastic degrees of freedom. Numerical simulation for periodic and chaotic responses are conducted in order to analyze the influence of the pull-up maneuver on the dynamic behavior of the panel. Long-time histories phase-plane plots, and power spectra of the responses are presented. As the maneuver (load factor) increases, the system exhibits complicated dynamic behavior including a direct and inverse cascade of subharmonic bifurcations, intermittency, and chaos. Beside these classical routes of transition from a periodic state to chaos, our calculations suggest amplitude modulation as a possible new mode of transition to chaos. Consequently this research contributes to the understanding of the mechanisms through which the transition between periodic and strange attractors occurs in, dissipative mechanical systems. In the case of a prescribed time dependent maneuver, a remarkable transition between the different types of limit cycles is presented.Nomenclature
a
plate length
-
a
r
u
r
/h
-
D
plate bending stiffness
-
E
modulus of elasticity
-
g
acceleration due to gravity
-
h
plate thickness
- j1,j2,j3
base vectors of the body frame of reference
-
K
spring constant
-
M
Mach number
-
n
1 + 0/g
-
N
1
applied in-plane force
-
p–p
aerodynamic pressure
- P
pa
4/Dh
-
q
0/2
-
Q
r
generalized Lagrangian forces
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R
rotation matrix
-
R
4
N, a
2/D
-
t
time
-
kinetic energy
-
u
plate deflection
- u
displacement of the structure
-
u
r
modal amplitude
- v0
velocity
- x
coordinates in the inertial frame of reference
- z
coordinates in the body frame of reference
-
Ka/(Ka+Eh)
-
-
elastic energy
-
2qa
3/D
-
a/mh
-
Poisson's ratio
-
material coordinates
-
air density
- m
plate density
-
- r
prescribed functions
- r
sin(r z/a)
-
angular velocity
-
a/v0
-
skew-symmetric matrix form of the angular velocity 相似文献
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