全文获取类型
收费全文 | 388篇 |
免费 | 60篇 |
国内免费 | 60篇 |
专业分类
航空 | 277篇 |
航天技术 | 73篇 |
综合类 | 55篇 |
航天 | 103篇 |
出版年
2023年 | 10篇 |
2022年 | 9篇 |
2021年 | 12篇 |
2020年 | 7篇 |
2019年 | 11篇 |
2018年 | 7篇 |
2017年 | 10篇 |
2016年 | 12篇 |
2015年 | 15篇 |
2014年 | 14篇 |
2013年 | 7篇 |
2012年 | 13篇 |
2011年 | 21篇 |
2010年 | 20篇 |
2009年 | 13篇 |
2008年 | 21篇 |
2007年 | 22篇 |
2006年 | 21篇 |
2005年 | 24篇 |
2004年 | 17篇 |
2003年 | 15篇 |
2002年 | 18篇 |
2001年 | 8篇 |
2000年 | 23篇 |
1999年 | 13篇 |
1998年 | 25篇 |
1997年 | 23篇 |
1996年 | 16篇 |
1995年 | 16篇 |
1994年 | 17篇 |
1993年 | 13篇 |
1992年 | 5篇 |
1991年 | 6篇 |
1990年 | 9篇 |
1989年 | 12篇 |
1988年 | 3篇 |
排序方式: 共有508条查询结果,搜索用时 15 毫秒
501.
502.
503.
《中国航空学报》2023,36(1):201-215
Flow instability of supercritical hydrocarbon fuel is a crucial issue in scramjet regenerative cooling structure. In this study, flow excursion instability and flow distribution in parallel tubes were experimentally studied for supercritical fluids. Two types of flow excursion occur in a single tube. Type I and Type II excursions, and they are corresponding to decreasing and increasing flow rate respectively. They can trigger flow maldistribution between parallel tubes and the hysteresis phenomenon of flow distribution. The effects of system parameters, including inlet temperature, system pressure, and heat flux, on flow distribution were analyzed. In addition, the relationship between flow excursion and the pseudo-critical interval proposed in the literature was established according to the heated tube outlet temperature at the onset of flow instability. Finally, the flow excursion instability boundary was obtained using two dimensionless parameters. These experimental results can provide helpful insight on the mechanism of Scramjet regenerative cooling. 相似文献
504.
《中国航空学报》2023,36(8):91-100
Aiming at the safety problem of the stage separation of parallel reusable high-speed air vehicles, this paper studies the unsteady test method and focuses on deriving a similarity law of parallel stage separation free-flight wind tunnel tests. The new similarity law considers the influences of aerodynamic force and gravity on the motions of the two stages, as well as the influence of aerodynamic interference between the two stages on each other’s motion. From the perspective of multi-angle physical equations, the conditions to ensure that the two-stage separation trajectory of a wind tunnel test is similar to that of a real air vehicle are derived innovatively, so as to ensure the authenticity and credibility of wind tunnel test results. The similarity law is verified by an HIFiRE-5 air vehicle, and the separation trajectories of wind tunnel tests and the real air vehicle are obtained by numerical simulation. The research shows that the similarity law derived in this paper can ensure that wind tunnel free-flight tests have the ability to predict the two-stage separation characteristics of real parallel vehicles. By analyzing the separation trajectory curve of the typical state, it is found that the new method can ensure that the trajectory error of a wind tunnel test does not exceed 1%, which indicates that this method is credible. The establishment of the new method lays the foundation for subsequent wind tunnel tests and provides support for research on the safety of the stage separation of parallel reusable air vehicles. 相似文献
505.
针对无人战斗机系统维护和飞行训练耗费巨大的问题,借鉴缩比模型验证机飞行试验的思路,研制具有相同飞行性能和操纵特性的缩比训练机。应用相似性原理,通过相似参数分析获得了缩比机与全尺寸原型机的飞行范围。在缩比机几何外形的基础上,应用Gridgen软件创建机体周围流场的非结构网格。通过Fluent软件,计算了缩比机纵向气动特性。根据俯仰力矩系数估算出全机气动中心位置,为缩比机的操纵性稳定性研究和控制率设计奠定了基础。 相似文献
506.
《中国航空学报》2023,36(3):171-183
The lander with orientation capability is of fundamental importance for the “Returning” mission because its body can be the base with a suitable launching angle for the ascender lifting off. This paper proposes the conceptual design and verification of Landers with Orientation Capability (LOCs). Firstly, the topological composition of the lander is analyzed and expressed in the form of Lie group, which provides the fundamental principle for the type synthesis of LOCs. Then, the type synthesis approach for designing LOCs is proposed, which includes designing the Equivalent Parallel Mechanism (EPM) and the auxiliary limbs. Numerous mechanisms of LOCs with two-dimensional rotational motions are obtained based on the type synthesis approach by developing and combining the EPMs and auxiliary limbs. Afterward, kinematics and Jacobian matrix of a typical legged lander are developed, the workspace is analyzed, singularity configurations are analyzed based on the wrench graph method, and finally, the orientation capability is analyzed. The pitch and yaw angle reach 17.5°, considering the permissible range of joints. The proposed types of LOCs offer potential candidate for the “Returning” mission of the exploration mission. 相似文献
507.
In the present study, an efficient overset grid method by means of parallel implicit hole-cutting is proposed for the sake of simulating unsteady flows in aerospace engineering involving multiple bodies in relative movement. In view of the degraded computational efficiency and robustness for conventional overset grid assembly, several innovative techniques are developed within the overset grid assembly process, viz., a bookkeeping alternative digital tree method to speed up the donor-cell search... 相似文献
508.