全文获取类型
收费全文 | 749篇 |
免费 | 114篇 |
国内免费 | 156篇 |
专业分类
航空 | 377篇 |
航天技术 | 353篇 |
综合类 | 50篇 |
航天 | 239篇 |
出版年
2024年 | 1篇 |
2023年 | 11篇 |
2022年 | 20篇 |
2021年 | 38篇 |
2020年 | 28篇 |
2019年 | 28篇 |
2018年 | 27篇 |
2017年 | 36篇 |
2016年 | 29篇 |
2015年 | 35篇 |
2014年 | 61篇 |
2013年 | 58篇 |
2012年 | 58篇 |
2011年 | 54篇 |
2010年 | 66篇 |
2009年 | 75篇 |
2008年 | 49篇 |
2007年 | 36篇 |
2006年 | 36篇 |
2005年 | 28篇 |
2004年 | 14篇 |
2003年 | 20篇 |
2002年 | 24篇 |
2001年 | 21篇 |
2000年 | 21篇 |
1999年 | 18篇 |
1998年 | 10篇 |
1997年 | 7篇 |
1996年 | 17篇 |
1995年 | 14篇 |
1994年 | 16篇 |
1993年 | 13篇 |
1992年 | 19篇 |
1991年 | 6篇 |
1990年 | 6篇 |
1989年 | 7篇 |
1988年 | 3篇 |
1987年 | 2篇 |
1984年 | 7篇 |
排序方式: 共有1019条查询结果,搜索用时 93 毫秒
511.
512.
高能脉冲X射线辐照材料时,能量沉积会使材料表层发生气化,并在材料内部形成高压热击波。目前一般采用差分方法对高压热击波过程进行数值模拟。文章尝试采用光滑粒子流体动力学(SPH)方法对X射线辐照材料进行数值模拟,由于材料表层的气化膨胀所致,膨胀后的粒子体积是原来的几十倍甚至上百倍,产生粒子大变形的粒子穿透现象;分析了产生粒子穿透现象的主要原因是气化边界处密度计算公式不合适所致,为此对密度计算公式进行了改进,并开展了基于改进密度计算公式的两种方法的数值模拟,两种方法的计算结果比较一致。 相似文献
513.
用于电子设备或系统辐射发射趋势预测的数据大多呈现非线性、样本量小的特点,这大大增加了预测建模的难度,而经验模态分解(EMD)可以将非线性、非平稳的数据分解成若干个呈现一定周期性的本征模态函数(IMF),并且EMD具有完备性和正交性,可通过分别对分解得到的IMF分量建模,从而完成对原始数据的建模。但EMD被端点效应问题所困扰,为了提高EMD的分解精度,针对分解过程中的端点效应问题,以及辐射发射趋势预测的时间序列数据样本量小的特点,利用建立灰色均值GM(1,1)预测模型所需数据量小的优点,提出了一种基于灰色均值GM(1,1)预测模型的边界延拓方法,在原始数据两端各拓展一个极大值和一个极小值,对原始数据进行边界延拓,从而抑制EMD的端点效应。仿真对比结果表明:该方法在分解层数和平均相对误差方面均优于未经延拓处理的EMD,且对数据样本量要求不高。 相似文献
514.
515.
Experimental investigation of transient thermal behavior of an airship under different solar radiation and airflow conditions 总被引:1,自引:0,他引:1
De-Fu Li Xin-Lin Xia Chuang Sun 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
Knowledge of the thermal behavior of airships is crucial to the development of airship technology. An experiment apparatus is constructed to investigate the thermal response characteristics of airships, and the transient temperature distributions of both hull and inner gas are obtained under the irradiation of a solar simulator and various airflow conditions. In the course of the research, the transient temperature change of the experimental airship is measured for four airflow speeds of 0 m/s (natural convection), 3.26 m/s, 5.5 m/s and 7.0 m/s, and two incident solar radiation values of 842.4 W/m2 and 972.0 W/m2. The results show that solar irradiation has significant influence on the airship hull and inner gas temperatures even if the airship stays in a ground airflow environment where the heat transfer is dominated by radiation and convection. The airflow around the airship is conducive to reduce the hull temperature and temperature nonuniformity. Transient thermal response of airships rapidly varies with time under solar radiation conditions and the hull temperature remains approximately constant in ∼5–10 min. Finally, a transient thermal model of airship is developed and the model is validated through comparison with the experimental data. 相似文献
516.
517.
518.
基于数据网格化方法的低轨辐射带建模技术 总被引:1,自引:0,他引:1
地球辐射带中的高能带电粒子是引起航天器材料和器件性能退化甚至失效的主要空间环境因素.因此,航天器设计中所采用的辐射带模型的准确程度对于航天器的生存能力和航天任务的完成质量至关重要.在利用我国自主辐射带高能粒子探测数据进行的辐射带建模中,探测数据的空间网格化是一项非常重要的工作.介绍了我国辐射带探测数据的情况,以及辐射带建模的方法和步骤;重点研究了不同插值方法在低地球轨道(LEO)空间辐射带建模数据网格化中的应用,并开展了误差分析.研究结果表明:在各种常用的插值方法中,反距离加权法、自然邻点法和最近邻点法适合工程化应用.其中,反距离加权法生成的数据网格对粒子通量的反演结果精度最高,该方法采用低阶距离时得到的反演结果更为合理. 相似文献
519.
On the practical exploitation of perturbative effects in low Earth orbit for space debris mitigation
Volker Schaus Elisa Maria Alessi Giulia Schettino Alessandro Rossi Enrico Stoll 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(7):1979-1991
This paper presents the results of a numerical evaluation of the natural lifetime reduction in low Earth orbit, due to dynamical perturbations. The study considers two values for the area-to-mass ratio, a nominal ratio which resembles a typical value of spacecraft in orbit today, and an enhanced ratio which covers the surface augmentation. The results were obtained with two orbit propagators, one of a semi-analytical nature and the second one using non-averaged equations of motion. The simulations for both propagators were set up similarly to allow comparison. They both use the solar radiation pressure and the secular terms of the geopotential ( and ). The atmospheric drag was turned on and off in both propagators to alternatively study the eccentricity build up and the residual lifetime. The non-averaging case also covers a validation with the full 6?×?6 geopotential. The results confirm the findings in previous publications, that is, the possibility for de-orbiting from altitudes above the residual atmosphere if a solar sail is deployed at the end-of-life, due to the combined effect of solar radiation pressure and the oblateness of the Earth. At near polar inclinations, shadowing effects can be exploited to the same end. The results obtained with the full, non-averaging propagator revealed additional de-orbiting corridors associated with solar radiation pressure which were not found by previous work on space debris mitigation. The results of both tools are compared for specific initial conditions. For nominal values of area-to-mass ratio, instead, it is confirmed that this resonance effect is negligible.The paper then puts the findings in the perspective of the current satellite catalogue. It identifies space missions which are currently close to a resonance corridor and shows the orbit evolution within the resonances with a significantly shorter residual orbital lifetime. The paper finishes with a discussion on the exploitation of these effects with regards to the long-term simulation of the space debris environment and a flux and collision probability comparison. 相似文献
520.
Stefan Gohl Benedikt Bergmann Hugh Evans Petteri Nieminen Alan Owens Stanislav Posipsil 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(5):1646-1660
We present the analysis of data taken by the Space Application of Timepix Radiation Monitor (SATRAM). It is centred on a Timepix detector (300?m thick silicon sensor, pixel pitch 55?m, 256?×?256 pixels). It was flown on Proba-V, an Earth observing satellite of the European Space Agency (ESA) from an altitude of 820?km on a sun-synchronous orbit, launched on May 7, 2013. A Monte Carlo simulation was conducted to determine the detector response to electrons (0.5–7?MeV) and protons (10–400?MeV) in an omnidirectional field taking into account the shielding of the detector housing and the satellite. With the help of the simulation, a strategy was developed to separate electrons, protons and ions in the data. The measured dose rate and stopping power distribution are presented as well as SATRAM’s capability to measure some of the stronger events in Earth’s magnetosphere. The stopping power, the cluster height and the shape of the particle tracks in the sensor were used to separate electrons, protons and ions. The results are presented as well. Finally, the pitch angles for a short period of time were extracted from the data and corrected with the angular response determined by the simulation. 相似文献