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81.
本文讨论了采用有限元法对具有进动的高速旋转的轴对称体进行应力分析的方法,首先,推导了轴对称体中哥氏惯性力的分布公式,在柱坐标系下,哥氏力中含有沿径向的零阶对称不载荷和沿轴向的一阶对称及一载荷,首次,采用了具有计算精度,对边界适应性强的八节点四边等参数环形单元,并将受哥氏惯性力的轴对称体看作非轴对称问题,对有限元分析中位移模式的建立和哥氏惯性力的处理作了讨论。最后,简要地说明了所研制的计算机程序,并 相似文献
82.
本文在建立坐标系的基础上 ,对杆件的内力、外力的符号进行了简单、明确的统一规定 ,从而使杆件三种基本变形和平面刚架结构的内力分析统一用同一种方法完成。这种方法克服了过去存在的内力计算和内力图绘制方法的多样性、规定不统一、难以识记的缺点 ,具有概念清晰、计算简便、工作流程固定统一的优点 ,便于学校师生和广大工程技术人员学习和掌握 ,编制上机操作程序简单易行。 相似文献
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84.
干涉SAR相位展开算法的比较和改进 总被引:1,自引:1,他引:1
基于残差理论深入分析和比较了 2种最主要的干涉 SAR相位展开方法积分路径法和最小均方法的策略及性能。对加权最小均方算法从初始值和权值进行了讨论,给出了一种合成加权多重网格算法。该算法结合了分支阻断方法简单快速并有一致解的特点,使它为多重网格最小均方算法提供初始值,加速了多重网格算法的收敛;并采用由相位导数方差生成的二值质量图替代相关系数作为权值输入,增强了算法的适应能力及可靠性。实际 X-SAR数据的相位展开处理结果验证了本文的分析和结论。 相似文献
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Electromagnetic formation flight(EMFF) leverages electromagnetic force to control the relative position of satellites. EMFF offers a promising alternative to traditional propellant-based spacecraft flight formation. This novel strategy is very attractive since it does not consume fuel. Due to the highly coupled nonlinearity of electromagnetic force, it is difficult to individually design a controller for one satellite without considering others, which poses challenges to communications.This paper is devoted to decoupling control of EMFF, including regulations, constraints and controller design. A learning-based adaptive sliding mode decoupling controller is analyzed to illustrate the problem of existing results, and input rate saturation is introduced to guarantee the validity of frequency division technique. Through transformation, the imposed input rate saturation is converted to state and input constraints. A linear matrix inequalities(LMI)-based robust optimal control method can then be used and improved to solve the transformed problem. Simulation results are presented to demonstrate the effectiveness of the proposed decoupling control. 相似文献
87.
N. Mireault G. Abel L. Andrzejewski G.G. Ross 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008,41(12):2150-2160
A setup called Controlled Rotation of Liquids (CROL) has been developed and used to investigate rotational behavior of liquids interacting with solids under reduced gravity conditions. The CROL setup allows us to evaluate the acceleration needed to overcome the interfacial forces that hinder liquid displacement inside different size containers. The well known Wilhelmy equation is used to explain the experimental results. Comparison between experimental results and theoretical predictions are presented and discussed. 相似文献
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89.
《中国航空学报》2020,33(1):88-101
Introducing flexibility into the design of a vertically flapping wing is an effective way to enhance its aerodynamic performance. As less previous studies on the aerodynamics of vertically flapping flexible wings focused on the lift generated in a wide range of angle of attack·a 2D numerical simulation of a purely plunging flexible airfoil is employed using a loose fluid–structure interaction method. The aerodynamics of a fully flexible airfoil are firstly studied with the flexibility and angle of attack. To verify whether an airfoil could get aerodynamic benefit from the change in structure, partially flexible airfoil with rigid leading edge and flexible trailing edge were further considered. Results show that flexibility could always reduce airfoil drag while lift and lift efficiency both peak at moderate flexibility. When freestream velocity is constant, lift is maximized at a high angle of attack about 40° while this optimal angle of attack reduces to 15° in drag-balanced status. The airfoil drag reduction, lift augmentation as well as efficiency enhancement mainly attribute to the passive pitching other than the camber deformation. Partially deformed airfoil with the longest length of moderate flexible trailing edge can achieve the highest lift. This study may provide some guidance in the wing design of Micro Air Vehicle (MAV). 相似文献
90.
分析了CDM方法的发展过程和基本设计思路,提出了基于CDM方法控制需要解决的三个问题,即系统稳定指数的优化选择、结构解耦分式约束条件设计、控制器的参数选择策略,同时给出了采用粒子群(PSO)优化算法的解决思路,并以此对直接力/气动力导弹复合控制进行了设计。仿真结果表明,即使在大攻角下控制器仍具有很强的鲁棒性。 相似文献