首页 | 本学科首页   官方微博 | 高级检索  
文章检索
  按 检索   检索词:      
出版年份:   被引次数:   他引次数: 提示:输入*表示无穷大
  收费全文   381篇
  免费   35篇
  国内免费   99篇
航空   351篇
航天技术   98篇
综合类   23篇
航天   43篇
  2023年   9篇
  2022年   10篇
  2021年   20篇
  2020年   21篇
  2019年   15篇
  2018年   20篇
  2017年   12篇
  2016年   20篇
  2015年   25篇
  2014年   19篇
  2013年   16篇
  2012年   28篇
  2011年   27篇
  2010年   29篇
  2009年   27篇
  2008年   35篇
  2007年   35篇
  2006年   35篇
  2005年   19篇
  2004年   21篇
  2003年   17篇
  2002年   21篇
  2001年   6篇
  2000年   9篇
  1999年   4篇
  1998年   2篇
  1997年   3篇
  1996年   1篇
  1995年   1篇
  1994年   1篇
  1992年   3篇
  1991年   1篇
  1990年   1篇
  1989年   2篇
排序方式: 共有515条查询结果,搜索用时 0 毫秒
511.
针对一类存在外界干扰和未建模动态的非线性不定系统,特别是含线性定常的参数不确定性及状态关联的非线性不确定性系统,应用直接自适应控制方法,设计了基于李雅普诺夫稳定性理论的鲁棒自适应控制律和修正律;应用李雅普诺夫稳定判据,对系统的稳定性进行了分析,证明所设计的控制律和修正律具有较强的鲁棒稳定性。  相似文献   
512.
《中国航空学报》2023,36(3):16-29
Geometric and working condition uncertainties are inevitable in a compressor, deviating the compressor performance from the design value. It’s necessary to explore the influence of geometric uncertainty on performance deviation under different working conditions. In this paper, the geometric uncertainty influences at near stall, peak efficiency, and near choke conditions under design speed and low speed are investigated. Firstly, manufacturing geometric uncertainties are analyzed. Next, correlation models between geometry and performance under different working conditions are constructed based on a neural network. Then the Shapley additive explanations (SHAP) method is introduced to explain the output of the neural network. Results show that under real manufacturing uncertainty, the efficiency deviation range is small under the near stall and peak efficiency conditions. However, under the near choke conditions, efficiency is highly sensitive to flow capacity changes caused by geometric uncertainty, leading to a significant increase in the efficiency deviation amplitude, up to a magnitude of ?3.6%. Moreover, the tip leading-edge radius and tip thickness are two main factors affecting efficiency deviation. Therefore, to reduce efficiency uncertainty, a compressor should be avoided working near the choke condition, and the tolerances of the tip leading-edge radius and tip thickness should be strictly controlled.  相似文献   
513.
《中国航空学报》2023,36(3):254-270
Planetary craters are natural navigation landmarks that widely exist and are easily observed. Optical navigation based on crater landmarks has become an important autonomous navigation method for planetary landing. Due to the increase in observed crater landmarks and the limitation of onboard computation, the selection of good crater landmarks has gradually become a research hotspot in the field of landmark-based optical navigation. This paper designs a fast crater landmark selection method, which not only considers the configuration observability of crater subsets but also focuses on the influence on navigation performance arising from the measurement uncertainty and the matching confidence of craters, which is different from other landmark selection methods. The factor of measurement uncertainty, which is anisotropic, correlated and nonidentically distributed, is quantified and integrated into selection based on crater pairing detection and localization error evaluation. In addition, the concept of the crater matching confidence factor is introduced, which reflects the possibility of 2D projection measurements corresponding to 3D positions. Combined with the configuration observability factor, the crater landmark selection indicator is formed. Finally, the effectiveness of the proposed method is verified by Monte Carlo simulations.  相似文献   
514.
合成孔径雷达(Synthetic Aperture Radar,SAR)影像变化检测是遥感领域的一个重要研究方向。文章以投票法(Majority Voting,MV)为基础,提出一种全新的顾及不确定性分析的SAR影像变化检测方法(Uncertainty Analysis-based MV,UAMV)。首先选取三组典型的差分影像生成算法,生成三组互补的差分影像。然后使用模糊C均值聚类估算每组差分影像的关于变化类和未变化类的模糊隶属度函数。最后用模糊集合和信息熵理论优化MV,构建顾及不确定性分析的多数投票法,并用所构建方法融合三组差分影像的模糊隶属度函数,生成变化检测图。为验证文章方法的有效性,通过三组真实SAR影像数据进行实验分析。实验结果表明:1)通过用信息熵分析MV融合过程中的不确定性,能够显著提高MV的变化检测性能;2)与7种现有相关算法相比,UAMV方法能够取得更优的变化检测结果。该研究为SAR影像变化检测提供一种新的思路和方法。  相似文献   
515.
In this paper, to solve the problem of parameters uncertainty in spacecraft tracking control, an adaptive controller based on sliding mode is proposed for the relative spacecraft attitude-orbit dynamics on the Lie group SE(3). The dynamic equations of relative attitude orbit error for two spacecraft are established in the framework of Lie group SE(3). Considering the uncertainty of spacecraft parameters, a formal decomposition of known and unknown parameters, the state variables and control variables is firstly made in the original system. An online estimator is designed to evaluate the unknown parameters. A sliding mode controller is developed to actuate the spacecraft to track the target spacecraft. Then a Lyapunov function of tracking error and parameters estimated error is designed to prove the stability of the closed-loop system. Finally, the simulation results and analysis are presented to verify the effectiveness and feasibility of the proposed method.  相似文献   
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号