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911.
912.
在经典排序问题中,工件的加工时间往往是一个常数,但在现代生产过程中,工件的加工时间受许多因素的影响。因此,研究工件具有学习效应的单机可控加工时间排序问题,其中工件的加工时间是其所在位置的函数,且与加工时间的控制变量有关。目标是求出最优的加工时间控制变量和最优的排序使得目标函数最小,目标函数包括极小化时间表长与控制费用的和、极小化总完工时间与控制费用的和、极小化总完工时间偏差和与控制费用和。证明他们都能转化为指派问题,从而多项式时间可解。并给出数值例子来说明问题是如何求解的。 相似文献
913.
利用诱导空间非相干技术平滑的KrF准分子(248nm)激光驱动带有烧蚀层的平面靶,研究激光空间均匀性对产生完整飞片的影响,结果表明激光不均匀性在2%以下,能够产生完整的高速飞片,且完整飞片能够维持20ns以上不破裂;当激光不均匀性达到5%,激光引入流体力学不稳定性种子应很强,冲击波在靶内输运过程中不稳定性不断发展增强,到靶背时强到足以使飞片解体甚至气化,不能产生完整的飞片。为了获得尽可能高的飞片速度,采用激光与烧蚀层参数不匹配方法,使冲击波对飞片作多次加速。利用功率密度为1012 W/cm2的KrF激光与含50μm Kapton烧蚀层的5μm铝飞片作用,得到速度约10km/s的高速飞片,与模拟结果吻合得很好。 相似文献
914.
P. Pappa Kalaivani O. Prakash Li Feng A. Shanmugaraju Liu-Guan Ding Lei Lu Weiqun Gan 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(10):3390-3403
We have established a data set of 58 major hybrid SEP events associated with meter-to-decahectometer wavelength (m-to-DH) type II bursts, solar flares, and radio-load CMEs during the period of 1997–2014. The main focus of our study is to address the following two questions: Does the interaction of CMEs play a role in the enhancement of SEP intensity? Is there any difference in the seed population, and parent eruptions in the SEP events with and without CME interactions? Hence, the sample of 58 events is classified into two sets: (i) 35 non-interacting-CME-associated SEP events; (ii) 23 interacting-CME-associated SEP events. All the characteristics of SEPs, their associated CMEs/flares and the relationships between them are statistically analyzed and compared. Some of the basic attributes and relative elemental abundances (Fe/O ratios) of the both the sets are also compared. The results indicate that the seed particles in non-interacting-CME-associated SEP events are mostly from solar wind/coronal materials. But in the case of interacting-CME-associated SEP events, it may be associated with both flare material from preceding flares and coronal materials from solar wind/preceding CMEs. The correlation studies reveal that there are clear correlations between logarithmic peak intensity of SEP events and properties of CMEs (space speed: cc?=?0.56) and solar flares (peak intensity: cc?=?0.40; integrated flux: cc?=?0.52) for non-interacting-CME-associated SEP events. But these correlations are absent for the interacting-CME-associated events. In addition, the results suggest that interaction of primary CMEs with their preceding CMEs plays an important role in the enhancement of peak intensity of SEPs at least for a set of m-to-DH type II bursts associated SEP events. 相似文献
915.
<正>沿袭多年的传统飞机蒙皮化铣加工工艺,由于化学污染、耗电量大和消耗铝材无法回收等固有弊病而成为该行业的一项困扰。对于加工新一代铝锂合金蒙皮来说,化铣还需采取防燃防爆的特别措施,从而增加 相似文献
916.
传统直升机气动设计较多依赖升力线理论、涡流理论等工程分析方法,高性能计算使采用CFD方法开展"第一性原理"仿真成为可能.本文从旋翼运动特点出发介绍了直升机区别于固定翼飞机的一些特殊计算方法,指出当前CFD方法在直升机实际应用中存在的不足.在此基础上,探讨了国外先进直升机CFD软件的发展策略与技术途径,从多求解器耦合、网格动态自适应技术、高阶格式与湍流模型的选取、多学科耦合求解等四个方面分析了这些软件的特点与技术优势.最后就如何适应未来发展需要,提出了直升机CFD能力建设方面的几点建议.分析表明,直升机由于旋翼运动具有与操纵输入、结构变形相耦合的特点,分部件及单学科的CFD分析方法与真实飞行状态存在偏差,多学科耦合分析与旋翼尾迹的精细模拟应当是软件未来发展的重点. 相似文献
917.
Prospects of using a permanent magnetic end effector to despin and detumble an uncooperative target 总被引:1,自引:0,他引:1
Xiaoguang Liu Yong Lu Yu Zhou Yuanhao Yin 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(8):2147-2158
Space debris, such as defunct satellites and upper stages of rockets, becomes an uncooperative target after losing its attitude control and communication ability. In addition, tumbling motion can occur due to environmental perturbations and residual angular momentum prior to the object’s end-of-mission. To minimize the collision risk during docking and capturing of the tumbling target, a non-contact method based on the eddy current effect is put forward to transmit the control torque to the tumbling target. The main idea is to induce a controllable torque on the conducting surface of the tumbling target using a rotational magnetic field generated by a Halbach rotor. The radial and axial Halbach rotors are used to damp the spinning and nutation motions of the target, respectively. The normal and tangential force are evaluated concerning the relative pose between the chaser and the target. A simplified dynamic model of the nutation damping and despinning processes is developed and the influences of the asymmetrical principal moments of inertia and transverse angular velocity are discussed. The numerical simulation results show that the designed Halbach rotor stabilized the target attitude within an acceptable time. The electromagnetic nutation damping and despinning method provides new solutions for the development of on-orbit capture technology. 相似文献
918.
919.
杨璐 《西安航空技术高等专科学校学报》2014,(5):93-96
随着我国研究生规模不断扩大,研究生培养本科化倾向严重,研究生就业、感情、科学研究等方面引发的心理问题不断增加,已影响到研究生的培养、发展,也影响到研究生自身的健康成长。对研究生心理健康问题的表现及成因进行分析,提出切实可行的对策措施,以期有效解决研究生心理健康问题,不断提升研究生的培养质量。 相似文献
920.
Lu Cao Xiaoqian Chen Arun K. Misra 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
Attitude determination is one of the key technologies for Attitude Determination and Control System (ADCS) of a satellite. However, serious model errors may exist which will affect the estimation accuracy of ACDS, especially for a small satellite with low precision sensors. In this paper, a central difference predictive filter (CDPF) is proposed for attitude determination of small satellites with model errors and low precision sensors. The new filter is proposed by introducing the Stirling’s polynomial interpolation formula to extend the traditional predictive filter (PF). It is shown that the proposed filter has higher accuracy for the estimation of system states than the traditional PF. It is known that the unscented Kalman filter (UKF) has also been used in the ADCS of small satellites with low precision sensors. In order to evaluate the performance of the proposed filter, the UKF is also employed to compare it with the CDPF. Numerical simulations show that the proposed CDPF is more effective and robust in dealing with model errors and low precision sensors compared with the UKF or traditional PF. 相似文献