全文获取类型
收费全文 | 307篇 |
免费 | 66篇 |
国内免费 | 72篇 |
专业分类
航空 | 210篇 |
航天技术 | 68篇 |
综合类 | 62篇 |
航天 | 105篇 |
出版年
2024年 | 1篇 |
2023年 | 4篇 |
2022年 | 9篇 |
2021年 | 23篇 |
2020年 | 17篇 |
2019年 | 12篇 |
2018年 | 15篇 |
2017年 | 14篇 |
2016年 | 10篇 |
2015年 | 14篇 |
2014年 | 16篇 |
2013年 | 18篇 |
2012年 | 14篇 |
2011年 | 17篇 |
2010年 | 28篇 |
2009年 | 20篇 |
2008年 | 13篇 |
2007年 | 17篇 |
2006年 | 18篇 |
2005年 | 18篇 |
2004年 | 14篇 |
2003年 | 10篇 |
2002年 | 26篇 |
2001年 | 16篇 |
2000年 | 16篇 |
1999年 | 4篇 |
1998年 | 6篇 |
1997年 | 4篇 |
1996年 | 4篇 |
1995年 | 2篇 |
1994年 | 6篇 |
1993年 | 7篇 |
1992年 | 4篇 |
1991年 | 5篇 |
1990年 | 4篇 |
1989年 | 6篇 |
1988年 | 5篇 |
1987年 | 3篇 |
1986年 | 2篇 |
1985年 | 1篇 |
1983年 | 1篇 |
1982年 | 1篇 |
排序方式: 共有445条查询结果,搜索用时 899 毫秒
281.
Φ5m立式风洞尾旋试验技术 总被引:4,自引:1,他引:3
中国空气动力研究与发展中心于2005年建成了Φ5m立式风洞.该风洞的主要功能是开展飞机自由尾旋风洞实验研究.因此,飞机尾旋试验研究与风洞建设同步进行,并于Φ5m立式风洞建成时就进行了一期民机的自由尾旋试验.笔者着重介绍了本期飞机自由尾旋试验的试验方法、试验设备、图像采集与处理、动力相似模型设计以及飞机尾旋特性分析.通过LE-500飞机中俄自由尾旋对比试验结果分析表明:两座立式风洞中的同一飞机模型的尾旋试验结果具有较好的一致性,中国空气动力研究与发展中心Φ5m立式风洞具备了开展飞机自由尾旋试验研究的能力. 相似文献
282.
As the deployment, supporting, and stability mechanisms of satellite antennas, space-deployable mechanisms play a key role in the field of aerospace. In order to design truss deployable antenna supporting mechanisms with large folding rate, high accuracy, easy deployment and strong stability, aiming at the geometric division of the parabolic reflector, a novel method based on symmetric hexagonal division and its corresponding modular truss deployable antenna mechanism is proposed, and the original method based on asymmetric triangular division and its corresponding mechanisms are presented for comparative analysis. Then, the screw theory is employed to analyze the mobility of different mechanisms. Furthermore, the improved three-dimensional mesh method is used to divide the reflector surface of a large parabolic antenna designed by the two different methods, and the profile accuracy and the type of links are taken as the evaluation indexes to quantitatively analyze the division results. Finally, a three-dimensional model of the modular deployable mechanism based on the symmetric hexagonal design is developed, and the deployable mechanisms with different configurations based on the two design methods are compared and analyzed from the mechanical perspective. The research results provide a good theoretical reference for the design of deployable truss antenna mechanisms and their application in the aerospace field. 相似文献
283.
284.
285.
Inner wrinkling control in hydrodynamic deep drawing of an irregular surface part using drawbeads 总被引:2,自引:0,他引:2
Inner wrinkling phenomenon is more likely to develop during hydrodynamic deep drawing (HDD) of complicated component-forms due to the higher demand for controlling deformation sequences. Aiming at the problems in control of inner wrinkling for an irregular surface part featured with both concavity and convex, this research proposes an optimal design method of drawbead parameters to change the material flow. According to theoretical analysis of the mechanism of inner wrinkling, optimizing cavity pressure only is unreasonable to form a wrinkle-free deep-drawn part, so semi-circular drawbeads are employed. The effects of layout and height of drawbeads on forming results are discussed, and a process window is established based on evaluation indicators including the anti-wrinkle coefficient and the minimum wall thickness. Experiments are carried out to validate the process window, and the wall thickness and the wrinkle height are measured and compared with numerical findings. The results show that the anti-wrinkle ability of drawbeads weakens with increasing oblique angle and distance from the die center, while the wall thickness increases with increasing oblique angle and distance, and the inner wrinkling can be completely suppressed by drawbeads arranged in zones I and II with optimum penetration. 相似文献
286.
有限元分析求解的大型线性方程组.其系数矩阵中只有少量的元素不为零,是一个稀疏矩阵,而且一般都是对称的。求解过程中只存贮对称部分的非零元素,这种全稀疏存贮策略采用链表式管理,使存贮结构可以动态更改。在带双门槛值ICCG方法的基础上加上对角元修正策略,产生了一种改进的ICCG求解法,它不仅节省了存贮空间,而且便于元素的查询、插入和删除,提高了求解效率。这里也给出了验证算例。 相似文献
287.
航天器项目群管理模式探讨 总被引:1,自引:0,他引:1
阐述了我国现有航天器多项目管理的模式和特点,在分析我国航天器项目管理发展基础上,根据航天器研制任务急剧增长的情况提出了项目群管理的概念和项目群管理模式的思路,为寻找更好的适合航天器快速发展的项目管理方法提供参考。 相似文献
288.
本文计算了小展弦比机翼纵向和横侧气动特性,并计及涡破裂的影响。本方法以Purvis升力面理论和Polhamus吸力比拟为基础。并参照Lan方法进行大迎角特性修正。算例表明,本方法适用于小展弦比机翼气动特性的计算。 相似文献
289.
研究了空间通信用高速Reed-Solomon(255,223)码硬判决译码器的FPGA实现方法,提出一种新的纠错算法实现结构以最大程度提高译码器性能。设计中采用RiBM算法求解关键方程,并通过应用高速比特并行乘法器以及流水线和并行处理方法提高译码通过率。综合和测试验证结果显示,该译码器译码通过速率为1.7Gbit/s,译码延迟为296个时钟周期,优于目前同类型的RS译码器性能指标。 相似文献
290.
This article makes an investigation into the creep behavior and deformation features of FGH95 powder Ni-base superalloy by means of creep curves and microstructural observation. Results show that this superalloy exposes obvious sensibility to the applied temperature and stresses in the experimental range. Microstructure of the alloy consists of γ′ phase of various sizes and dispersed carbide particles precipitated in the wider crystal boundaries between the powder particles. During the creep, the deformation of the alloy occurs in the form of single- or double-oriented slipping inside the grains, and some of the finer carbide particles are precipitated near the slipping traces. The wide grain boundaries might be broken into the finer grains due to severe deformation. The deformation mechanism of the alloy during creep is thought to be the activation of dislocations of double-oriented slipping, including (1/2)<110> dislocation inside the γ matrix phase and <110> super-dislocation inside the γ′ phase. The formation of the stacking faults and (1/3)<112> super-Shockleys partial dislocation configuration is attributed to the decomposition of <110> super-dislocation in the γ′ phase. 相似文献