全文获取类型
收费全文 | 121篇 |
免费 | 44篇 |
国内免费 | 26篇 |
专业分类
航空 | 98篇 |
航天技术 | 44篇 |
综合类 | 4篇 |
航天 | 45篇 |
出版年
2023年 | 4篇 |
2022年 | 19篇 |
2021年 | 8篇 |
2020年 | 10篇 |
2019年 | 9篇 |
2018年 | 5篇 |
2017年 | 2篇 |
2016年 | 6篇 |
2015年 | 4篇 |
2014年 | 10篇 |
2013年 | 7篇 |
2012年 | 4篇 |
2011年 | 12篇 |
2010年 | 7篇 |
2009年 | 4篇 |
2008年 | 9篇 |
2007年 | 15篇 |
2006年 | 9篇 |
2005年 | 8篇 |
2004年 | 3篇 |
2003年 | 5篇 |
2002年 | 2篇 |
2001年 | 1篇 |
2000年 | 3篇 |
1999年 | 5篇 |
1998年 | 5篇 |
1997年 | 2篇 |
1996年 | 2篇 |
1994年 | 1篇 |
1993年 | 4篇 |
1992年 | 3篇 |
1989年 | 1篇 |
1988年 | 1篇 |
1984年 | 1篇 |
排序方式: 共有191条查询结果,搜索用时 46 毫秒
131.
Flight trajectory optimization of sun-tracking solar aircraft under the constraint of mission region
《中国航空学报》2021,34(11):140-153
The optimal yawing angle of sun-tracking solar aircraft is tightly related to the solar azimuth angle, which results in a large arc flight path to dynamically track the sun position. However, the limited detection range of payload usually requires solar aircraft to loiter over areas of interest for persistent surveillance missions. The large arc sun-tracking flight may cause the target area on the ground to be outside the maximum coverage area of payload. The present study therefore develops an optimal flight control approach for planning the flight path of sun-tracking solar aircraft within a mission region. The proposed method enables sun-tracking solar aircraft to maintain the optimal yawing angle most of the time during daylight flight, except when the aircraft reverses its direction by turning flight. For a circular region with a mission radius of 50 km, the optimal flight trajectory and controls of an example Λ-shaped sun-tracking solar aircraft are investigated theoretically. Results demonstrate the effectiveness of the proposed approach to optimize the flight path of the sun-tracking aircraft under the given circular region while maximizing the battery input power. Furthermore, the effects of varying the mission radius on energy performance are explored numerically. It has been proved that both net energy and energy balance remain nearly constant as the radius constraint varies, which enables the solar aircraft to achieve perpetual flight at almost the same latitude as the large arc flight. The method and results presented in this paper can provide reference for the persistent operation of sun-tracking solar aircraft within specific mission areas. 相似文献
132.
针对无人机(UAV)通信网络中频谱资源紧缺的问题,构建基于认知无线电的多无人机通信网络,通过多机协作频谱感知有效探索授权频谱。提出一种基于Bisection算法的迭代算法,通过联合优化感知时间和判决门限对构建的复杂非凸问题求解,显著提高了无人机次级认知网络的能量效率(EE)。分析了无人机飞行过程中能效的变化情况,仿真结果表明,存在最优感知时间使能效获得最大值,且判决门限的选择会影响该能效最优值;提出的高能效迭代算法具有较好收敛性,有效提高了认知无人机网络的能量利用率。 相似文献
133.
对CMA盲均衡技术在海上靶场遥测信号接收中的应用进行了仿真研究,同时在CMA盲均衡算法的基础上提出了一种能量匹配约束条件,对在能量匹配约束条件下的CMA算法进行了理论分析和算法推导。根据峰度准则,输入输出信号能量相等是盲均衡实现的充要条件的前提,依据这一前提,对CMA算法代价函数进行修正,有效提高了算法的收敛速度和均衡性能。 相似文献
134.
Resonance transitions associated to weak capture in the restricted three-body problem 总被引:1,自引:1,他引:0
Edward Belbruno Francesco Topputo Marian Gidea 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008,42(8):1330-1351
An interesting dynamics is studied in the restricted three-body problem where a particle abruptly transitions between resonance states, called a resonance hop. It occurs in a region about the secondary mass point which supports weak capture. This region, called a weak stability boundary, was recently proven to give rise to chaotic dynamics. Although it was numerically known that the resonance hop was associated with this boundary, this process was not well understood. In addition, the dynamical structure of the weak stability boundary has not been well understood. In this paper, we give a way to reveal the global structure of the weak stability boundary associated to resonance motions. This structure is shown to be surprisingly rich in resonant periodic motions interconnected by invariant manifolds. In this case, nearly all the motions are approximately resonant in nature where resonance hops can occur. The correlation dimension of orbits undergoing resonant motions, associated to the weak stability boundary, is also examined. The dynamics analyzed in the present paper is related to that studied by J. Marsden et al. under the perspective of Lyapunov orbits and the associated invariant manifolds. Applications are discussed. 相似文献
135.
136.
简述了超声疲劳试验机的工作原理以及应用超声疲劳试验技术研究工程结构材料疲劳裂纹扩展性能的实验方法。通过三维有限元计算及动态模态分析,研究了包括整体裂纹扩展试件及聚能器在内的振动体的应力、应变场和位移场,导出了确定裂纹尖端应力强度因子的位移法和能量法,并对这两种计算分析方法的特点以及所得到的结果进行了分析对比。计算与分析结果表明,应用能量法研究超声疲劳载荷下的裂纹尖端应力强度因子及疲劳裂纹扩展性能,具有简明和计算精度高等突出优点。 相似文献
137.
138.
V.V. Mishin V.M. Mishin Z. Pu S.B. Lunyushkin L.A. Sapronova U. Sukhbaatar D.G. Baishev 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
The magnetic flux of tail lobes Ψ is divided in two parts of comparable values Ψ1 and Ψ02, with the first that appears during substorm and the second, observed before substorm start. The first was named “new magnetic flux”, the second – “old magnetic flux”. The first, Ψ1, is known to play a definitive role in the energy transport from the solar wind into the magnetosphere-ionosphere-atmosphere system, but the role of Ψ02 in this transport is not well known. From the 27 August 2001 substorm data we study the involvement in the above transport process of the old flux Ψ02. This involvement is observed in the polar cap (PC) area, which existed prior to the substorm and is called respectively “the old PC”. In this study, as distinct from earlier works, we use the balance equation of the energy stored in magnetosphere and energy consumed. Activation of the old PC magnetic flux Ψ02 was found to increase the energy input by ∼85% in the event under consideration. 相似文献
139.
140.
为提高陶瓷基复合材料在轻质装甲结构设计中应用的可行性,研究陶瓷基复合材料在抵抗弹体撞击时的表面驻留性能,进而探索其抗弹性能,旨在丰富和完善陶瓷基复合装甲材料的抗弹机理。采用数模模拟方法对弹体撞击SiC-Al陶瓷基复合材料表面驻留过程开展了深入研究,探索了复合材料的表面驻留行为,对比分析了复合材料和陶瓷材料表面驻留过程中应力水平和损伤演化过程。结果表明:复合材料表面驻留耗能为845J,比B_4C、SiC、AD99Al_2O_3陶瓷材料分别提高约46.0%、30.2%、35.7%;完全损伤的复合材料仍具有较一般陶瓷材料更高的承载能力,延长其驻留持续时间;复合材料损伤演化形式与陶瓷材料差异较大,导致损伤耗能占总驻留耗能的比例达到23.9%,比陶瓷材料提高了2倍多。 相似文献