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   1467篇
  免费   335篇
  国内免费   341篇
航空   1233篇
航天技术   336篇
综合类   182篇
航天   392篇
  2024年   7篇
  2023年   31篇
  2022年   59篇
  2021年   97篇
  2020年   65篇
  2019年   129篇
  2018年   125篇
  2017年   105篇
  2016年   124篇
  2015年   102篇
  2014年   105篇
  2013年   101篇
  2012年   123篇
  2011年   140篇
  2010年   108篇
  2009年   92篇
  2008年   98篇
  2007年   90篇
  2006年   67篇
  2005年   65篇
  2004年   39篇
  2003年   41篇
  2002年   26篇
  2001年   35篇
  2000年   29篇
  1999年   19篇
  1998年   18篇
  1997年   19篇
  1996年   6篇
  1995年   10篇
  1994年   14篇
  1993年   11篇
  1992年   13篇
  1991年   9篇
  1990年   10篇
  1989年   8篇
  1988年   3篇
排序方式: 共有2143条查询结果,搜索用时 15 毫秒
861.
航天器姿态滑模变结构控制系统的设计   总被引:4,自引:0,他引:4  
给出了航天器三轴动力学和四元数姿态运动学方程。在分析滑模变结构控制的基本原理和设计方法的基础上,通过二次型最优法解出航天器姿态角速度与姿态角之间的函数关系,进而得到滑动平面。在此基础上,应用滑模变结构控制方法对航天器姿态控制系统进行了设计和仿真,并与PID控制系统进行了分析比较。仿真结果表明,滑模控制系统具有良好的动态品质和稳态性能,体现了变结构控制的突出优点,对系统摄动和外加干扰具有极强的鲁棒性和自适应性。  相似文献   
862.
波片堆作为理想的耦合模式传递标准已被国外许多著名校准机构采用。对采用波片堆研制偏振模色散传递标准的原因,及其设计、制备和装配的全过程进行了叙述;并对其研制过程中遇到的技术难点和解决方法进行了介绍;最后简述了波片堆偏振模色散传递标准的适用性和实验结果。  相似文献   
863.
大客发动机径向传动杆具有长径比大、转速高等特点.为保证传动杆可靠工作,需进行精确的动态特性分析,而边界条件的选取和简化是保证传动杆动态特性准确性的关键.分别使用了简化模型和整体模型计算了传动杆的模态,通过边界条件的选取设置,对传动杆进行了动态特性分析和试验验证,并与试验结果进行了对比.结果显示,使用整体模型计算得到的传动杆模态振型与试验结果较为一致,证明了传动杆边界条件选取方法的正确性.  相似文献   
864.
In this study, a two-step control methodology is developed for energy-optimal reconfiguration of satellites in formation in the presence of uncertainties or external disturbances. First, based on a linear deterministic system model, an optimal control law is analytically determined such that a satellite maneuvers from an initial state to a final state relative to another satellite. The structure of this optimal solution is predetermined and simply given by a linear combination of the fundamental matrix solutions associated with the original equations of relative motion. Only the coefficients are to be determined to satisfy given initial and final conditions. In the second step, an uncertain nonlinear formation system is considered and a robust adaptive controller is designed to compensate for the effects of uncertainties or disturbances that the formation system may encounter. Although the control strategy is inspired by sliding mode control, it produces smooth control signals, thereby avoiding chattering. Also, an adaptation law is added such that the uncertainty or disturbance effects are effectively and quickly eliminated without a priori information about them. The combination of these two controllers guarantees that the satellite accurately tracks the optimal path in the unknown environment. Numerical simulations demonstrate the effectiveness and accuracy of the proposed two-step control methodology, in which a satellite formation is optimally reconfigured under unknown environmental disturbances.  相似文献   
865.
An effective 3D supersonic Mach box approach in combination with non-classical hybrid metal-composite plate theory has been used to investigate flutter boundaries of trapezoidal low aspect ratio wings. The wing structure is composed of two main components including alu-minum material (in-board section) and laminated composite material (out-board section). A global Ritz method is used with simple polynomials being employed as the trial functions. The most important objective of the present research is to study the effect of composite to metal proportion of hybrid wing structure on flutter boundaries in low supersonic regime. In addition, the effect of some important geometrical parameters such as sweep angle, taper ratio and aspect ratio on flutter boundaries were studied. The results obtained by present approach for special cases like pure metal-lic wings and results for high supersonic regime based on piston theory show a good agreement with those obtained by other investigators.  相似文献   
866.
生产准备是影响航空产品快速切换的主要环节.为实现航空产品在MBD模式下的快速切换,剖析了航空产品生产准备的主要内容,探讨了MBD模式下航空产品生产准备信息传递模式以及影响航空产品生产过程快速切换的关键因素.  相似文献   
867.
Mode shape has become a hotspot of vibration-based damage detection in plates.Two-dimensional(2D)modal curvature(MC2D),derived from mode shapes,is a prevailing physical quantity used to indicate damage.Unfortunately,the physical mechanism of MC2 Dfor characterizing damage in plates has not been clarified to date.In contrast,one-dimensional(1D)modal curvature(MC1D)has explicit physical mechanism to portray damage in beams.Unresolved physical mechanism of MC2 Dseverely hampers its applications for damage identification in plates.To address this deficiency,the clarification mechanism of MC2 Dis investigated to identify damage.With the clarified mechanism,numerical and experimental cases are used to demonstrate the effectiveness of MC2 Din detecting damage in plates.  相似文献   
868.
本文介绍一种利用电报头接口改造旧电火花线切割机床,通过CAXA软件实现线切割数控系统与计算机的通信,充分发挥CAXA绘图式自动编程软件的优点,实现旧设备的升级改造。  相似文献   
869.
Adaptive sliding mode control for limit protection of aircraft engines   总被引:1,自引:1,他引:1  
In practice, some sensors of aircraft engines naturally fail to obtain an acceptable measurement for control propose, which will severely degrade the system performance and even deactivate the limit protection function. This paper proposes an adaptive strategy for the limit protection task under unreliable measurement. With the help of a nominal system, an online estimator with gradient adaption law and low-pass filter is devised to evaluate output uncertainty. Based on the estimation result, a sliding mode controller is designed by defining a sliding surface and deriving a control law. Using Lyapunov theorem, the stability of the online estimator and the closed-loop system is detailedly proven. Simulations based on a reliable turbofan model are presented, which verify the stability and effectiveness of the proposed method. Simulation results show that the online estimator can operate against the measurement noise, and the sliding controller can keep relevant outputs within their limits despite slow-response sensors.  相似文献   
870.
陈弈澄  齐瑞云  张嘉芮  王焕杰 《航空学报》2019,40(7):322827-322827
针对采用太阳帆、太阳电混合小推力推进的航天器,研究了其在日心悬浮轨道的保持控制问题。为解决已有控制方法中未综合考虑内部未建模动态和外部未知扰动的问题,以及进一步提高系统控制性能,设计了一种高性能滑模控制策略。首先,考虑模型不确定性,建立了混合小推力航天器在日心悬浮轨道柱面坐标系的动力学方程;其次,基于改进型条件积分滑模面和径向基(RBF)神经网络设计了控制律,结合自适应方法在线估计不确定参数;接着,将求取的虚拟控制量在推进剂最优条件下转换成实际控制量,即太阳帆姿态角和太阳电推进力;最后,数值仿真验证了上述设计方法提高了系统鲁棒性,减小了轨道位置超调,并且混合推进相比于单一太阳帆推进,在更短收敛时间内控制精度提高了4个数量级,相比于单一太阳电推进,一年可以节省约89.6%的推进剂。  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