全文获取类型
收费全文 | 2052篇 |
免费 | 391篇 |
国内免费 | 600篇 |
专业分类
航空 | 981篇 |
航天技术 | 719篇 |
综合类 | 177篇 |
航天 | 1166篇 |
出版年
2024年 | 13篇 |
2023年 | 56篇 |
2022年 | 77篇 |
2021年 | 148篇 |
2020年 | 95篇 |
2019年 | 137篇 |
2018年 | 146篇 |
2017年 | 122篇 |
2016年 | 133篇 |
2015年 | 143篇 |
2014年 | 267篇 |
2013年 | 172篇 |
2012年 | 186篇 |
2011年 | 166篇 |
2010年 | 149篇 |
2009年 | 154篇 |
2008年 | 131篇 |
2007年 | 99篇 |
2006年 | 93篇 |
2005年 | 83篇 |
2004年 | 46篇 |
2003年 | 67篇 |
2002年 | 57篇 |
2001年 | 42篇 |
2000年 | 54篇 |
1999年 | 38篇 |
1998年 | 26篇 |
1997年 | 19篇 |
1996年 | 16篇 |
1995年 | 17篇 |
1994年 | 15篇 |
1993年 | 11篇 |
1992年 | 8篇 |
1991年 | 11篇 |
1990年 | 11篇 |
1989年 | 9篇 |
1988年 | 8篇 |
1987年 | 1篇 |
1986年 | 1篇 |
1985年 | 16篇 |
排序方式: 共有3043条查询结果,搜索用时 515 毫秒
131.
132.
133.
Vitali Braun A. LüpkenS. Flegel J. GelhausM. Möckel C. KebschullC. Wiedemann P. Vörsmann 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Today’s space debris environment shows major concentrations of objects within distinct orbital regions for nearly all size regimes. The most critical region is found at orbital altitudes near 800 km with high declinations. Within this region many satellites are operated in so called sun-synchronous orbits (SSO). Among those, there are Earth observation, communication and weather satellites. Due to the orbital geometry in SSO, head-on encounters with relative velocities of about 15 km/s are most probable and would thus result in highly energetic collisions, which are often referred to as catastrophic collisions, leading to the complete fragmentation of the participating objects. So called feedback collisions can then be triggered by the newly generated fragments, thus leading to a further population increase in the affected orbital region. This effect is known as the Kessler syndrome. 相似文献
134.
William P. Schonberg 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
Spacecraft that are launched to operate in Earth orbit are susceptible to impacts by meteoroids and pieces of orbital debris (MMOD). The effect of a MMOD particle impact on a spacecraft depends on where the impact occurs, the size, composition, and speed of the impacting object, the function of the impacted system. In order to perform a risk analysis for a particular spacecraft under a specific mission profile, it is important to know whether or not the impacting particle (or its remnants) will exit the rear of an impacted spacecraft wall. A variety of different ballistic limit equations (BLEs) have been developed for many different types of structural wall configurations. BLEs can be used to optimize the design of spacecraft wall parameters so that the resulting configuration is able to withstand the anticipated variety of on-orbit high-speed impact scenarios. While the level of effort exerted in studying the response of metallic multi-wall systems to high speed particle impact is quite substantial, the extent of the effort to study composite material and composite structural systems under similar impact conditions has been much more limited. This paper presents an overview of the activities performed to assess the resiliency of composite structures and materials under high speed projectile impact. The activities reviewed will be those that have been aimed at increasing the level of protection afforded to spacecraft operating in the MMOD environment, and more specifically, on those activities performed to mitigate the mechanical and structural effects of an MMOD impact. 相似文献
135.
136.
A. Lukaszczyk R. Williamson 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
Non-governmental organizations (NGOs) play a unique role in international affairs, providing access to resources, expertise, and assistance to supplement State resources. Sometimes the diplomatic skills and unofficial access of NGOs to policymakers through Track Two diplomacy can move a previously stalled critical issue forward and assist policymakers from different countries to find common ground outside official channels. Because they work outside of official channels, they are not bound by State policy that may inhibit negotiations between States. Some also have a convening power that sometimes makes it possible for State representatives to meet discipline experts and each other for informal discussions on issues of mutual interest. Finally, NGOs can draw attention to issues that may be overlooked or avoided by State organizations. 相似文献
137.
T. Hopf S. KumarW.J. Karl W.T. Pike 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
It is often necessary for space-borne instrumentation to cope with substantial levels of shock acceleration both in the initial launch phase, as well as during entry, descent and landing in the case of planetary exploration. Current plans for a new generation of penetrator-based space missions will subject the associated on-board instrumentation to far greater levels of shock, and ways must therefore be found to either ruggedize or else protect any sensitive components during the impact phase. In this paper, we present an innovative method of shock protection that is suited for use in a number of planetary environments, based upon the temporary encapsulation of said components within a waxy solid which may then be sublimated to return the instrument back to its normal operation. We have tested this method experimentally using micromachined silicon suspensions under applied shock loads of up to 15,000g, and found that these were able to survive without incurring damage. Furthermore, quality factor measurements undertaken on these suspensions indicate that their mechanical performance remains unaffected by the encapsulation and subsequent sublimation process. 相似文献
138.
给出了一种求解严格伪压缩非自身映像不动点集上变分不等式的迭代算法,并证明了其强收敛性。此结果推广了姚永红和T.H.Kim等的研究结果。最后,进一步将结论推广到求解有限个严格伪压缩非自身映像公共不动点集上的变分不等式。 相似文献
139.
一种新型燃烧室供油系统热防护方案 总被引:1,自引:0,他引:1
武禹张净玉李季骆东 《南京航空航天大学学报》2016,48(3):366-371
随着航空发动机燃烧室进口空气温度的不断升高,燃油在供油管路内受热氧化结焦从而引发诸多隐患的情况日益突出。本文针对某型中心分级、多点喷射供油系统,开展了以空气隔热屏结合“油冷”的热防护方案设计研究,并通过数值
模拟分析了热防护效果。研究表明,在典型高温进气工况下,空气隔热屏结构可将燃油管路湿壁温度降低至燃油氧化结焦临界温度以下;在慢车主油路停止供油的情况下,单一的空气隔热措施难以满足热防护设计要求,结合“油冷”方案可达到设计要求。 相似文献
140.
我国未来深空探测工程的发展对地基深空站发射机提出了更高的要求,不仅仅需要具有更高的输出功率,同时需要解决发射机高频谱纯度、高效率以及上行功率合成等。针对这些要求,对国内外地基深空网的组成和深空站高功率发射机现状以及未来发展趋势进行了研究,分析了速调管发射机与固态发射机在高功率输出条件下的优势,在此基础上,提出了我国深空站速调管发射机需要开展高功率连续波速调管、高功率低损耗滤波器、低纹波高功率开关电源、上行功率合成等关键技术,并为相应关键技术提供了理论建议及相应的解决方法,这可以为我国未来深空探测工程高功率发射机研制提供技术支撑,为后续地基深空网建设和发展提供参考。 相似文献