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291.
A novel model-based multivariable framework for aircraft gas turbine engine limit protection control
《中国航空学报》2021,34(12):57-72
Control technologies are innovated to satisfy increasingly complicated control demands of gas turbine engines. In terms of limit protection control, a novel model-based multivariable limit protection control method, which is achieved by adaptive command reconstruction and multiple-control loop selection and switch logic, is proposed in this paper to address the problem of balancing smaller thrust loss and safe operations by comparing with widely-used Min-Max logic. Five different combination modes of control loops, which represent the online control loop of last time instant and that of current time instant, is analyzed. Different command reconstructions are designed for these modes, which is based on static gain conversion of amplitude beyond limits by using an onboard model. The double-prediction based control loop selection and switch logic is developed to choose a control loop appropriately by comparing converted amplitude beyond limits regardless of one or more parameters tending to exceed limits. The proposed method is implemented in a twin-spool turbofan engine to achieve limit protection with direct thrust control, and the loss of thrust is improved by about 30% in comparison with the loss of thrust caused by Min-Max logic when limit protection control is activated, which demonstrates the effectiveness of the proposed method. 相似文献
292.
《中国航空学报》2021,34(5):265-277
Severe stress concentration occurs around circular vent holes of an industrial turbine sealing disk. This paper investigates the structural design and optimization for the vent holes to effectively reduce the maximum von Mises stress and improve the fatigue life of the turbine sealing disk. An efficient integrated design optimization method is presented based on a novel non-circular vent hole design method in combination with a variable dimension sub-model method, a self-developed modeling and meshing tool, and the Multi-Island Genetic Algorithm. The proposed non-circular vent hole is biaxial symmetric and consists of four smoothly connected arcs. The variable dimension sub-model method is utilized to obtain accurate results in the fields around the vent holes within the computationally acceptable time. The modeling and meshing tool is developed by using the Tcl/Tk Scripts to rebuild the geometry and generate the high-quality hexahedral mesh automatically. The Multi-Island Genetic Algorithm is adopted to solve the studied constrained optimization problem. After optimization, the maximum von Mises stress is reduced from 1305.644 MPa to 963.435 MPa, and the fatigue life is increased from 3091 cycles to 30,297 cycles. The results show that the proposed design and optimization methods can significantly improve the performance of the turbine sealing disk along with the remarkable drop in stress concentration. 相似文献
293.
为了获得回流型脉冲爆震燃烧室在不同工作频率下的工作特性,通过试验和数值相结合的方法对该爆震室工作频率10~30Hz时的出口燃气总压、总温、流量变化规律以及该爆震室的增压能力进行了测试与计算分析。结果表明:出口燃气总压、总温具有极高的峰值和较高的平台区,其工作频率10~30Hz时,压力平台值为0.36~0.91MPa,时均温度为710~1270K。此外,该爆震室排气流量十分集中,以10Hz为例,在一个爆震循环的16%时间,排出了整个循环60.5%的燃气。为此对出口燃气总压进行质量加权平均,发现该爆震室的增压比随工作频率的增加而降低,在2.37~2.05之间。 相似文献
294.
为了探究船舶燃气轮机内部冷却通道的颗粒沉积特性,本研究从随压气机抽取的气体进入冷却涡轮内部冷却通道内的颗粒动力学特性及颗粒与壁面相互作用特性出发,基于高温壁面建立速度场影响的沉积模型,利用用户自定义函数实现沉积模型与CFD程序的嵌套。并简化船舶燃气轮机内部冷却通道,选取了在气膜孔与壁面之间夹角β=90°时,下游肋倾角α不同(α=30°,45°,60°,75°,90°),及在下游肋倾角α=60°时,气膜孔与壁面之间夹角β不同(β=30°,45°,60°,75°,90°)的八种不同内冷结构进行数值计算。研究表明,在气膜孔与壁面之间夹角β=90°不变时,随着下游肋倾角由α=90°减到α=30°时,弯头壁面换热性能和沉积率逐渐呈下降趋势,下游肋与肋之间壁面上颗粒的撞击率逐渐上升。下游肋倾角α=60°,气膜孔与壁面之间夹角β=45°的U型肋通道,在八个内冷结构中弯头壁面沉积率最少,换热性能最好,是能够有效改善船舶燃气轮机冷却涡轮的海洋环境工作适应性,减少内部冷却通道中颗粒沉积的内冷结构。 相似文献
295.
296.
I. Zhelyazkov T.V. Zaqarashvili L. Ofman R. Chandra 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(2):628-638
We investigate the conditions under which the fluting (), , and magnetohydrodynamic (MHD) modes in a uniformly twisted flux tube moving along its axis become unstable in order to model the Kelvin–Helmholtz (KH) instability in a twisting solar coronal hole jet near the northern pole of the Sun. We employed the dispersion relations of MHD modes derived from the linearized MHD equations. We assumed real wavenumbers and complex angular wave frequencies, namely complex wave phse velocities. The dispersion relations were solved numerically at fixed input parameters (taken from observational data) and varying degrees of torsion of the internal magnetic field. It is shown that the stability of the modes depends upon five parameters: the density contrast between the flux tube and its environment, the ratio of the external and internal axial magnetic fields, the twist of the magnetic field lines inside the tube, the ratio of transverse and axial jet’s velocities, and the value of the Alfvén Mach number (the ratio of the tube axial velocity to Alfvén speed inside the flux tube). Using a twisting jet of 2010 August 21 by SDO/AIA and other observations of coronal jets we set the parameters of our theoretical model and have obtained that in a twisted magnetic flux tube of radius of Mm, at a density contrast of and fixed Alfvén Mach number of , for the three MHD modes there exist instability windows whose width crucially depends upon the internal magnetic field twist. It is found that for the considered modes an azimuthal magnetic field of – G (computed at the tube boundary) makes the width of the instability windows equal to zero, that is, it suppress the KH instability onset. On the other hand, the times for developing KH instability of the MHD mode at instability wavelengths between 15 and 12 Mm turn out to be in the range of – min that is in agreement with the growth rates estimated from the temporal evolution of the observed unstable jet’s blobs in their initial stage. 相似文献
297.
用非线性线弹簧模型,对含有表面裂纹的球瓶破坏性实验结果进行了弹塑性断裂力学分析。讨论了对宇航薄壁压力容器表面裂纹建立安全评定标准的必要性。采用线弹性断裂力学分析方法可能给出危险的结果。将J_(m.d.p)=J_(IC)作为宇航压力容器表面裂纹弹塑性断裂的判据,具有准确,简便的优点。 相似文献
298.
孙巨峰 《西安航空技术高等专科学校学报》2002,20(1):29-31
本篇通过燃气燃烧特性的分析,指出了强化燃烧的措施,并通过燃气燃烧污染因素的分析,指出了污染控制的措施。 相似文献
299.
含钉孔有限大板应力集中系数解法—解析最小二乘法 总被引:2,自引:0,他引:2
在研究孔边应力集中系数的问题中,利用了复变函数方法,设预先满足所有的基本方程的待定复函数,再利用最小二乘法使其满足边界条件,从而解出孔边应力集中系数。 相似文献
300.