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861.
任意轮廓线图形的快速扫描线转换 总被引:2,自引:0,他引:2
多边形的扫描线转换和区域填充是光栅图形面着色的两种主要方法。前者速度快,但对多边形轮廓线的形状有一定要求;后者无此限制,但须访问区域内的所有象素点,填充速度慢。本文基于对轮廓形状信息的分析,提出了一种任意封闭轮廓线图形的快速扫描线转换方法,它无需访问映象内存即可完成任意封闭轮廓线图形的扫描线转换,保持了多边形的扫描线转换与区域种子填充两种方法的优点,避免了各自的不足,因此具有更一般的应用适应性及更高的转换效率。 相似文献
862.
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
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865.
Hancheol Cho 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(5):1454-1467
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
866.
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
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868.
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
869.
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
870.
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