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61.
介绍了国产变极性等离子弧焊(VPPAW)设备的组成、变极性电源主电路的工作原理。以及微机控制和焊炬等关键技术。用该设备对不同厚度的高强度可热处理强化铝合金试样、贮箱缩比及1:1试验件进行了VPPAW,并分析了接头形式、起弧与收弧、焊接工艺参数确定、常见缺陷、焊接组织及其力学性能。焊接试验结果表明,用VPPAW设备焊接的铝舍金厚度可达14mm,与交流钨极惰性气体保护焊(TIG)相比,其焊缝质量佳,接头性能优。 相似文献
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主要研究卫星远距离稳态伴飞的控制问题。首先,根据线性相对运动方程(C-W方程)设计了能实现稳态伴飞的变结构控制律,并证明了其在有干扰情况下的有效性。然后,推导了适用于远距离相对运动的非线性方程解析解,并在此基础上对伴飞控制律进行了改进,以实现远距离的稳态伴飞。通过仿真,比较了上述控制律的效果,证明了基于非线性相对运动的变结构控制能有效地实现远距离稳态伴飞。 相似文献
65.
It has been well known that nozzle end-clearances in a Variable Nozzle Turbine (VNT) are unfavorable for aerodynamic performance, especially at small openings, and efforts to further decrease size of the clearances are very hard due to thermal expansion. In this paper, both the different sizes of nozzle end-clearances and the various ratios of their distribution at the hub and shroud sides were modelled and investigated by performing 3D Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) simulations with a code of transferring the aerodynamic pressure from the CFD results to the FEA calculations. It was found that increasing the size of the nozzle end-clearances divided equally at the hub and shroud sides deteriorates turbine efficiency and turbine wheel reliability, yet increases turbine flow capacity. And, when the total nozzle end-clearances remain the same, varying nozzle end-clearances’ distribution at the hub and shroud sides not only shifts operation point of a VNT turbine, but also affects the turbine wheel vibration stress. Compared with nozzle hub clearance, the shroud clearance is more sensitive to both aerodynamic performance and reliability of a VNT turbine. Consequently, a possibility is put forward to improve VNT turbine efficiency meanwhile decrease vibration stress by optimizing nozzle end-clearances’ distribution. 相似文献
66.
Redundantly actuated planar rotational parallel mechanisms (RAPRPMs) adapt to the requirements of robots under different working conditions by changing the antagonistic internal force to tune their stiffness. The geometrical parameters of the mechanism impact the performances of modulating stiffness. Analytical expressions relating stiffness and geometrical parameters of the mechanism were formulated to obtain the necessary conditions of variable stiffness. A novel method of variable stiffness design was presented to optimize the geometrical parameters of the mechanism. The stiffness variation with the internal force was maximized. The dynamic change of stiffness with the dynamic location of the mechanism was minimized, and the robustness of stiff-ness during the motion of the mechanism was ensured. This new approach to variable stiffness design can enable off-line planning of the internal force to avoid the difficulties of on-line control of the internal force. 相似文献
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Uttam Kumar S. Kumar Raja Chiranjit Mukhopadhyay T.V. Ramachandra 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Variable Endmember Constrained Least Square (VECLS) technique is proposed to account endmember variability in the linear mixture model by incorporating the variance for each class, the signals of which varies from pixel to pixel due to change in urban land cover (LC) structures. VECLS is first tested with a computer simulated three class endmember considering four bands having small, medium and large variability with three different spatial resolutions. The technique is next validated with real datasets of IKONOS, Landsat ETM+ and MODIS. The results show that correlation between actual and estimated proportion is higher by an average of 0.25 for the artificial datasets compared to a situation where variability is not considered. With IKONOS, Landsat ETM+ and MODIS data, the average correlation increased by 0.15 for 2 and 3 classes and by 0.19 for 4 classes, when compared to single endmember per class. 相似文献
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Young-Joo Song Sang-Young Park Kyu-Hong Choi Eun-Sup Sim 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2009
A design technique for a near optimal, Earth–Moon transfer trajectory using continuous variable low thrust is proposed. For the Earth–Moon transfer trajectory, analytical and numerical methods are combined to formulate the trajectory optimization problem. The basic concept of the proposed technique is to utilize analytically optimized solutions when the spacecraft is flying near a central body where the transfer trajectories are nearly circular shaped, and to use a numerical optimization method to match the spacecraft’s states to establish a final near optimal trajectory. The plasma thruster is considered as the main propulsion system which is currently being developed for crewed/cargo missions for interplanetary flight. The gravitational effects of the 3rd body and geopotential effects are included during the trajectory optimization process. With the proposed design technique, Earth–Moon transfer trajectory is successfully designed with the plasma thruster having a thrust direction sequence of “fixed-varied-fixed” and a thrust acceleration sequence of “constant-variable-constant”. As this strategy has the characteristics of a lesser computational load, little sensitivity to initial conditions, and obtaining solutions quickly, this method can be utilized in the initial scoping studies for mission design and analysis. Additionally, derived near optimal trajectory solution can be used as for initial trajectory solution for further detailed optimization problem. The demonstrated results will give various insights into future lunar cargo trajectories using plasma thrusters with continuous variable low thrust, establishing approximate costs as well as trajectory characteristics. 相似文献
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为了研究双外涵变循环压缩系统的涵道流动匹配规律,发展了涵道流动的计算模型,对压缩系统模式转换过程中外涵道倒流问题的发生机理和影响因素进行了深入分析,总结了压缩系统的倒流判断准则,并基于简化计算模型和全三维计算结果对倒流判据进行了验证。研究结果表明,对于一定的压缩系统匹配状态,存在一个决定涵道匹配状态的临界核心机驱动风扇级(Core Driven Fan Stage, CDFS)总压比,当CDFS的实际工作压比高于临界压比时,压缩系统第二外涵道将发生倒流,反之则系统不倒流。复杂涵道系统内的流动损失和堵塞等特性对临界CDFS总压比有显著影响,为了准确判断压缩系统的匹配状态,需要对其进行精确模化。基于简化模型得到的压缩系统倒流临界线可以推广至全三维状态,本文提出的倒流判别准则具有较高的可靠性和可行性。 相似文献