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《中国航空学报》2021,34(5):350-363
The interaction of an impinging oblique shock wave with an angle of 30° and a supersonic turbulent boundary layer at Ma∞=2.9 and Reθ = 2400 over a wavy-wall is investigated through direct numerical simulation and compared with the interaction on a flat-plate under the same flow conditions. A sinusoidal wave with amplitude to wavelength ratio of 0.26 moves in the streamwise direction and is uniformly distributed across the spanwise direction. The influences of the wavy-wall on the interaction, including the characterization of the flow field, the skin-friction, pressure and the budget of turbulence kinetic energy, are systematically studied. The region of separation grows slightly and decomposes into four bubbles. Local peaks of skin-friction are observed at the rear part of the interaction region. The low-frequency shock motion can be seen in the wall pressure spectra. Analyses of the turbulence kinetic energy budget indicate that both diffusion and transport significantly increase near the crests, balanced by an amplified dissipation in the near-wall region. Proper orthogonal decomposition analyses show that the most energetic structures are associated with the separated shock and the shear layer over the bubbles. Only the bubbles in the first two troughs are dominated by a low-frequency enlargement or shrinkage. 相似文献
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Shuang Li Yuming Peng 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
This paper addresses the issue of Mars atmospheric entry trajectory optimization by use of the desensitized optimal control (DOC) and Direct Collocation and Nonlinear Programming (DCNLP). Firstly, desensitized optimal control methodology is adopted to reduce the sensitivity of terminal state variables with respect to uncertainties and perturbations along the trajectory, in addition to optimizing the original performance index. Then, Direct Collocation (DC) method is used to transform the optimal control problem into Nonlinear Programming (NLP) problem which can be easily solved using the SNOPT software package. Monte Carlo simulations of error analysis show that the sensitivity of terminal state variables with respect to uncertainties and perturbations is significantly reduced, leading to improved entry precision. 相似文献
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A direct drive actuator (DDA) with direct drive valves (DDVs) as the control device is an ideal solution for a flight actuation system. This paper presents a novel triple-redundant voice coil motor (TRVCM) used for redundant DDVs. The TRVCM features electrical/mechanical hybrid triple-redundancy by securing three stators along with three moving coils in the same frame. A permanent magnet (PM) Halbach array is employed in each redundant VCM to simplify the system structure. A back-to-back design between neighborly redundancies is adopted to decouple the magnetic flux linkage. The particle swarm optimization (PSO) method is implemented to optimize design parameters based on the analytical magnetic circuit model. The optimization objective function is defined as the acceleration capacity of the motor to achieve high dynamic performance. The optimal geometric parameters are verified with 3D magnetic field finite element analysis (FEA). A research prototype has been developed for experimental purpose. The experimental results of magnetic field density and force output show that the proposed TRVCM has great potential of applications in DDA systems. 相似文献
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针对高空航天飞机等再入飞行器表面缺陷或防热瓦缝隙导致的局部压力过高和气动加热问题,采用直接模拟Monte Carlo (DSMC)方法研究了飞行高度为80 km的稀薄流区高超声速凹腔绕流问题,考虑气固相互作用(GSI)模型对凹腔流场特征和表面压力、热流的影响。结果表明:稀薄流条件(80 km)下,GSI为完全漫反射时,在凹腔前缘分离的剪切层再次附着在后缘,在凹腔内部形成一个充满腔体的单涡结构;随着GSI从完全漫反射向镜面反射变化,气体与凹腔表面之间的切向动量交换减弱,即黏性剪切作用减弱,外部气流被卷入凹腔的程度减弱,导致涡结构不断减小直至消失,凹腔底部逐渐出现所谓的"死水区"。与完全漫反射相比,镜面反射或近镜面反射会导致凹腔上游侧面的峰值压力和峰值热流以及下游侧面的峰值压力剧烈增大,在飞行器设计中,应特别留意上述表面的压力载荷和热载荷。 相似文献
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碳纳米管是一种有前途的微波吸收剂,可以作为潜在的隐身材料、电磁屏蔽材料或暗室吸波材料使用.本文综述了近年来国内外通过碳纳米管碳化学镀改性、纳米管与聚合物共混、纳米管与铁磁材料杂化来制备微波吸收剂的研究成果和存在的问题,提出了碳纳米管作为吸波材料今后的发展方向. 相似文献
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介绍了直接数字频率合成(DDS)技术工作原理及特点,给出了基于DDS设计的自动频率控制(AFC)系统的设计,形成一种能提供稳定频率的具有宽频带跟踪范围的AFC系统,并对其进行了性能分析。 相似文献