全文获取类型
收费全文 | 1819篇 |
免费 | 533篇 |
国内免费 | 316篇 |
专业分类
航空 | 1500篇 |
航天技术 | 408篇 |
综合类 | 188篇 |
航天 | 572篇 |
出版年
2024年 | 11篇 |
2023年 | 43篇 |
2022年 | 102篇 |
2021年 | 126篇 |
2020年 | 128篇 |
2019年 | 98篇 |
2018年 | 84篇 |
2017年 | 119篇 |
2016年 | 94篇 |
2015年 | 138篇 |
2014年 | 176篇 |
2013年 | 164篇 |
2012年 | 176篇 |
2011年 | 163篇 |
2010年 | 139篇 |
2009年 | 156篇 |
2008年 | 133篇 |
2007年 | 111篇 |
2006年 | 112篇 |
2005年 | 60篇 |
2004年 | 49篇 |
2003年 | 34篇 |
2002年 | 36篇 |
2001年 | 31篇 |
2000年 | 25篇 |
1999年 | 31篇 |
1998年 | 24篇 |
1997年 | 23篇 |
1996年 | 19篇 |
1995年 | 10篇 |
1994年 | 10篇 |
1993年 | 9篇 |
1992年 | 6篇 |
1991年 | 8篇 |
1990年 | 10篇 |
1989年 | 4篇 |
1988年 | 3篇 |
1987年 | 2篇 |
1986年 | 1篇 |
排序方式: 共有2668条查询结果,搜索用时 281 毫秒
71.
72.
73.
Reconfigurable Flight Control Design for Combat Flying Wing with Multiple Control Surfaces 总被引:2,自引:2,他引:0
With control using redundant multiple control surface arrangement and large-deflection drag rudders,a combat flying wing has a higher probability for control surface failures.Therefore,its flight control system must be able to reconfigure after such failures.Considering three types of typical control surface failures(lock-in-place(LIP),loss-of-effectiveness(LOE) and float),flight control reconfiguration characteristic and capability of such aircraft types are analyzed.Because of the control surface redundancy,the aircraft using the dynamic inversion flight control law already has a control allocation block.In this paper,its flight control configuration during the above failures is achieved by modifying this block.It is shown that such a reconfigurable flight control design is valid,through numerical simulations of flight attitude control task.Results indicate that,in the circumstances of control surface failures with limited degree and the degradation of the flying quality level,a combat flying wing adopting this flight control reconfiguration approach based on control allocation could guarantee its flight safety and perform some flight combat missions. 相似文献
74.
N2O-C2H2原子吸收光谱法测定卫星系统电池外壳铝合金中的硅含量。讨论了燃烧器高度、燃助比、共振线等测定条件的选择方法,以及酸度、温度和N2O-C2H2火焰区对测定精度的影响。实际应用证明,该方法灵敏度高,干扰小,选择性和重复性好,并具有操作简便,易掌握,分析周期短等特点;精密度和准确度均能满足卫星系统电池外壳体研制的要求。 相似文献
75.
圆截面曲线管道内二次流动的Galerkin解 总被引:4,自引:2,他引:2
本文推导了曲线直角坐标系内的N-S方程。结果表明Galerkin方法可以克服摄动法的小参数局限,得到了纯数值法无法求得的增 解析解。 相似文献
76.
77.
Aerodynamic optimization design for high pressure turbines based on the adjoint approach 总被引:2,自引:1,他引:1
A first study on the continuous adjoint formulation for aerodynamic optimization design of high pressure turbines based on S2surface governed by the Euler equations with source terms is presented.The objective function is defined as an integral function along the boundaries,and the adjoint equations and the boundary conditions are derived by introducing the adjoint variable vectors.The gradient expression of the objective function then includes only the terms related to physical shape variations.The numerical solution of the adjoint equation is conducted by a finitedifference method with the Jameson spatial scheme employing the first and the third order dissipative fluxes.A gradient-based aerodynamic optimization system is established by integrating the blade stagger angles,the stacking lines and the passage perturbation parameterization with the quasi-Newton method of Broyden–Fletcher–Goldfarb–Shanno(BFGS).The application of the continuous adjoint method is validated through a single stage high pressure turbine optimization case.The adiabatic efficiency increases from 0.8875 to 0.8931,whilst the mass flow rate and the pressure ratio remain almost unchanged.The optimization design is shown to reduce the passage vortex loss as well as the mixing loss due to the cooling air injection. 相似文献
78.
介绍了一种应用于人工辅助心脏的永磁轴承无位置传感器盘式无刷直流电动机的结构与电磁场仿真计算方法及结果,并对其温度场进行仿真计算。该电机体积重量小,无机械轴承,避免了对血液的破坏,且运行安全可靠。 相似文献
79.
80.