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Optimal guidance based on receding horizon control for low-thrust transfer to libration point orbits
Haijun Peng Qiang Gao Zhigang Wu Wanxie Zhong 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
This paper addresses the design and computation of a guidance law for a transfer mission from an orbit near the Earth to a halo orbit around the libration point L2 in the Sun–Earth system. The guidance law, which is designed based on receding horizon control and compensates for launch velocity errors that are introduced by inaccuracies of the launch vehicle, is solved using the generating function method. During the design of the closed-loop guidance law, the entire transfer mission, which is considered a nonlinear optimal control problem, is evaluated to obtain a nominal reference trajectory. Using the launch velocity errors and the uncertainty of the model, a spacecraft controlled by the proposed guidance law tracks the reference trajectory. Furthermore, the original Riccati differential equation in the receding horizon control algorithm is replaced by an equivalent convenient form of the Riccati differential equation that is based on the generating function. The high-efficiency solution of the equivalent equation avoids the online direct integration of the original Riccati differential equation, which significantly increases the computational efficiency for the receding horizon control problem. Numerical simulations using a nonlinear bicircular four-body model demonstrate the capabilities of the proposed receding horizon guidance law for the transfer mission. In addition, the generating function method improves the computational efficiency by at least one order of magnitude over the backward sweep method in solving the receding horizon control problem. 相似文献
393.
Long term dynamics and optimal control of nano-satellite deorbit using a short electrodynamic tether 总被引:1,自引:0,他引:1
R. Zhong Z.H. Zhu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
This paper studies the long term dynamics and optimal control of a nano-satellite deorbit by a short electrodynamic tether. The long term deorbit process is discretized into intervals and within each interval a two-phase optimal control law is proposed to achieve libration stability and fast deorbit simultaneously. The first-phase formulates an open-loop fast-deorbit control trajectory by a simplified model that assumes the slow-varying orbital elements of electrodynamic tethered system as constant and ignores perturbation forces other than the electrodynamic force. The second phase tracks the optimal trajectory derived in the first phase by a finite receding horizon control method while considering a full dynamic model of electrodynamic tether system. Both optimal control problems are solved by direct collocation method base on the Hermite–Simpson discretization schemes with coincident nodes. The resulting piecewise nonlinear programing problems in the sequential intervals reduces the problem size and improve the computational efficiency, which enable an on-orbit control application. Numerical results for deorbit control of a short electrodynamic tethered nano-satellite system in both equatorial and highly inclined orbits demonstrate the efficiency of the proposed control method. An optimal balance between the libration stability and a fast deorbit of satellite with minimum control efforts is achieved. 相似文献
394.
便携式相控阵探伤仪在复合材料检测中的应用 总被引:1,自引:0,他引:1
相控阵探伤仪能够通过图像的形式直观地显示缺陷,并通过线性B扫描图或扇形图显示一定区域范围内的缺陷,有利于对缺陷的评判. 相似文献
395.
Talso C P Chui Inseob Hahn Konstantin Penanen Fang Zhong Donald Strayer 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2005,36(1):99-106
We discuss how superconductivity and superfluidity can be applied to solve the challenges in the exploration of the Moon and Mars. High sensitivity instruments using phenomena of superconductivity and superfluidity can potentially make significant contributions to the fields of navigation, automation, habitation, and resource location. Using the quantum nature of superconductivity, lightweight and very sensitive diagnostic tools can be made to monitor the health of astronauts. Moreover, the Moon and Mars offer a unique environment for scientific exploration. We also discuss how powerful superconducting instruments may enable scientists to seek answers to several profound questions about nature. These answers will not only deepen our appreciation of the universe, they may also open the door to paradigm-shifting technologies. 相似文献
396.
基于小型三坐标测量机的机械研究 总被引:1,自引:1,他引:0
从三坐标测量机的实际设计出发,通过对小型三坐标测量机的机械分析和实验,对三坐标测量机的设计提供理论基础的分析和可行的思路。 相似文献
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从最基本的质心运动方程出发,通过飞机运动基本假设,运用相似原理和微分修正量法,推导出飞机水平加速性能向定高度换算的公式。结合某型飞机的试飞给出换算结果实例,并与以前换算方法得到的结果进行比较,说明此换算方法原理正确,可以为飞机性能研究人员提供参考。 相似文献
399.
杨中 《西安航空技术高等专科学校学报》2011,29(6):10-12
在我国高职高专教育事业蓬勃发展的同时,高职高专教育教学研究室院校学报已成长为一支生力军。高职高专院校学报既是各高职院校学术交流的宣传交流窗口,又是广大教师展示科研成果与技术创新成果的有效平台。学报的论文发表与交流,既可以提高教师的业务水平,又可以进一步提升学校教学、科研的整体水平,使学校形成一个良好的学术氛围,对推动高职高专教育的发展起到良好的促进作用。虽然高职高专院校学报起步晚,底子薄,经验少,但是依据自身的优势和地方特点,坚持特色办刊的理念,多数学报已经成为了独树一帜的学术交流平台。 相似文献
400.