全文获取类型
收费全文 | 2309篇 |
免费 | 742篇 |
国内免费 | 416篇 |
专业分类
航空 | 1892篇 |
航天技术 | 730篇 |
综合类 | 356篇 |
航天 | 489篇 |
出版年
2024年 | 9篇 |
2023年 | 41篇 |
2022年 | 105篇 |
2021年 | 103篇 |
2020年 | 126篇 |
2019年 | 117篇 |
2018年 | 91篇 |
2017年 | 85篇 |
2016年 | 116篇 |
2015年 | 112篇 |
2014年 | 129篇 |
2013年 | 134篇 |
2012年 | 166篇 |
2011年 | 165篇 |
2010年 | 144篇 |
2009年 | 125篇 |
2008年 | 103篇 |
2007年 | 126篇 |
2006年 | 123篇 |
2005年 | 85篇 |
2004年 | 97篇 |
2003年 | 126篇 |
2002年 | 104篇 |
2001年 | 73篇 |
2000年 | 95篇 |
1999年 | 83篇 |
1998年 | 92篇 |
1997年 | 64篇 |
1996年 | 94篇 |
1995年 | 74篇 |
1994年 | 72篇 |
1993年 | 60篇 |
1992年 | 53篇 |
1991年 | 46篇 |
1990年 | 55篇 |
1989年 | 38篇 |
1988年 | 26篇 |
1987年 | 8篇 |
1986年 | 2篇 |
排序方式: 共有3467条查询结果,搜索用时 991 毫秒
761.
A numerical study on flow control of ship airwake during shipboard landing is carried out to address the effect of flow control devices on helicopter rotor airload. The in-house Reynolds Averaged Navier-Stokes (RANS) based solver Rotorcraft AeroDynamics and Aeroacoustics Solver (RADAS), with combination of momentum source approach is employed to conduct the helicopter shipboard landing simulation. The control effects of three aerodynamic modifications of ship superstructure, i.e. ramp, notch and flap, in different Wind-Over-Deck (WOD) conditions are discussed. From the steady simulation results, the effect of spatial variation of ship airwake on rotor airloads is concluded. The aerodynamic modifications reduce the strength of shedding vortex and increase rotor normal force through delaying and relieving flow separation, and therefore are beneficial to alleviate the limitation of control inputs. By contrast, the perturbation of unsteady ship airwake can cause the serious oscillation of rotor forces during shipboard landing. The unsteady simulations show that the turbulence intensity of ship airwake and oscillatory rotor airloading, represented by Root-Mean-Square (RMS) loading, can be remarkably reduced by the ramp and notch modifications, while the flap modification has adverse effect. It means that flow control devices have large potential benefits to alleviate the pilot’s workload and improve the shipboard landing safety, but they should be well designed to avoid the introduction of more vortex, which leads to increase in disturbance of flow field. 相似文献
762.
763.
764.
本文描述用电子束辉光法测量高超声速流中平均密度、速度以及密度变化特征的物理原理和过程。对此法用于平板上激波层稳定性问题的适用范围和限制条件作了分析。内容通过风洞实验结果加以说明。 相似文献
765.
提出了一种基于Windows环境下的活塞裙部外圆复杂型面在位检测的新方法,并设计了在位检测的软、硬件系统.同时,根据活塞裙部型面的特点,在现有常用误差处理算法的基础上进行了改进,新的误差处理方法具有更强的适用性. 相似文献
766.
767.
分析了小角度正弦激光干涉仪的有关特性,叙述了这种方法的测量原理,计算了几种因素对测量准确度的影响,指出提高测量准确度的解决办法。 相似文献
768.
介绍了某型卫星测控雷达的校飞设备以及这些设备在某型飞机上的安装方案,并对方案进行了分析,确保方案的可行性。 相似文献
769.
In order to promote an in-depth understanding of the mechanism of leading-edge flow separation control over an airfoil using a symmetrical Dielectric Barrier Discharge(DBD) plasma actuator excited by a steady-mode excitation, an experimental investigation of an SC(2)-0714 supercritical airfoil with a symmetrical DBD plasma actuator was performed in a closed chamber and a low-speed wind tunnel. The plasma actuator was mounted at the leading edge of the airfoil.Time-resolved Particle Image Velocimetry(PIV) results of the near-wall region in quiescent air suggested that the symmetrical DBD plasma actuator could induce some coherent structures in the separated shear layer, and these structures were linked to a dominant frequency of f0= 39 Hz when the peak-to-peak voltage of the plasma actuator was 9.8 kV. In addition, an analysis of flow structures without and with plasma actuation around the upper side of the airfoil at an angle of attack of18° for a wind speed of 3 m/s(Reynolds number Re = 20000) indicated that the dynamic process of leading-edge flow separation control over an airfoil could be divided into three stages. Initially, this plasma actuator could reinforce the shedding vortices in the separated shear layer. Then, these vortical structures could deflect the separated flow towards the wall by promoting the mixing between the outside flow with a high kinetic energy and the flow near the surface. After that, the plasma actuator induced a series of rolling vortices in the vicinity of the suction side of the airfoil, and these vortical structures could transfer momentum from the leading edge of the airfoil to the separated region, resulting in a reattachment of the separated flow around the airfoil. 相似文献
770.
《中国航空学报》2020,33(5):1494-1504
Adapter ring is a commonly used component in non-cooperative satellites, which has high strength and is suitable to be recognized and grasped by the space manipulator. During proximity operations, this circle feature may be occluded by the robot arm or limited field of view. Moreover, the captured images may be underexposed when there is not enough illumination. To address these problems, this paper presents a structured light vision system with three line lasers and a monocular camera. The lasers project lines onto the surface of the satellite, and six break points are formed along both sides of the adapter ring. A closed-form solution for real-time pose estimation is given using these break points. Then, a virtual structured light platform is constructed to simulate synthetic images of the target satellite. Compared with the predefined camera parameters and relative positions, the proposed method is demonstrated to be more effective, especially at a close distance. Besides, a physical space verification system is set up to prove the effectiveness and robustness of our method under different light conditions. Experimental results indicate that it is a practical and effective method for the pose measurement of on-orbit tasks. 相似文献