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841.
针对垂直磨削中磨削痕迹分布规律不明晰而使得磨削表面质量难以准确控制的问题,开展垂直磨削中磨削参数对磨削痕迹分布规律影响的研究。依据单颗磨粒磨削痕迹分布方程、仿真分析和探讨了砂轮转速、工件转速、进给速度、转速比和相移对磨削痕迹分布的影响,基于磨削参数对磨削痕迹分布和残留高度的影响,优选出了磨削痕迹分布相对合理的磨削参数组合,并进行磨削加工对比实验。结果表明,垂直磨削法中,磨削参数通过改变磨削痕迹的长度、间距、数量、位置关系和分布情况等影响磨削后工件的表面质量。其中,相移的大小会影响磨削痕迹的首尾相接与相互错开情况,直接决定着磨削纹理的形成与否,进而成为影响磨削后工件表面质量的关键因素;此外,尽管磨削参数中工件转速相差很小,但磨削痕迹分布状况会出现显著的差异,进而导致工件表面纹理和破碎情况显著不同及表面粗糙度Ra存在59~125 nm的差距。因此,基于磨削参数对磨削痕迹分布的影响,合理的匹配磨削加工参数可大幅提高工件表面质量。 相似文献
842.
提出了结构缺陷敏感区域的概念。借助结构缺陷稳定分析的改进随机缺陷法,研究了单层网壳结构的缺陷敏感区域。通过50m跨度的K6型凯威特网壳算例,得出它的缺陷敏感区域由前12类结点组成。并发现支座结点缺陷对K6型凯威特单层网壳结构影响不大;而主肋上结点与次肋上结点的缺陷对K6型网壳的影响相似,均会使其临界荷载下降很多。结果证明该方法可定量和准确地分析结构的缺陷敏感区域。 相似文献
843.
《中国航空学报》2021,34(3):71-81
The aerodynamic performance of compressor airfoil is significantly affected by the surface roughness at low Reynolds number (Re). In the present study, numerical simulations have been conducted to investigate the impact of surface roughness on the profile loss of a high subsonic compressor airfoil at Re = 1.5 × 105. Four roughness locations, covering 10%, 30%, 50% and 100% of the suction surface from the leading edge and seven roughness magnitudes (Ra) ranging from 52 to 525 μm were selected. Results showed that the surface roughness mainly determined the loss generation process by influencing the structure of the Laminar Separation Bubble (LSB) and the turbulence level near the wall. For all the roughness locations, the variation trend for the profile loss with the roughness magnitude was similar. In the transitionally rough region, the negative displacement effect of the LSB was suppressed with the increase of roughness magnitude, leading to a maximum decrease of 14.6%, 16.04%, 16.45% and 10.20% in the profile loss at Ra = 157 μm for the four roughness locations, respectively. However, with a further increase of the roughness magnitude in the fully rough region, the stronger turbulent dissipation enhanced the growth rate of the turbulent boundary layer and increased the profile loss instead. By comparison, the leading edge roughness played a dominant role in the boundary layer development and performance variation. To take fully advantage of the surface roughness reducing profile loss at low Re, the effects of roughness on suppressing LSB and inducing strong turbulent dissipation should be balanced effectively. 相似文献
844.
845.
846.
《中国航空学报》2021,34(4):132-139
Profiled monolayer cBN wheel was induction brazed for grinding of titanium dovetail slot in this study. Aimed at acquiring a uniform temperature distribution along the profiled surface and reducing the thermal deformation of the brazed wheel, a finite element model was established to investigate the temperature uniformity during induction brazing. A suitable induction coil and the related working parameters were designed and chosen based on the simulation results. Ag-Cu-Ti alloy and cBN grains were applied in the induction brazing experiment. The results showed geometric deformation of the brazed wheel was no more than 0.01 mm and chemical reaction layer were found on the brazed joint interface. Further validation tests were carried out by grinding of Ti-6Al-4V alloy. Compared to the electroplated wheel, the brazed wheel showed better performance such as low specific grinding energy and good ground quality in grinding of Ti-6Al-4V alloy. Abrasion wear was found to be the main failure mode for the induction brazed wheel, while adhesion and grains pull-out were the main failure mode for the electroplated wheel. 相似文献
847.
848.
The study of the development cost of general aviation aircraft is limited by small samples with many cost-driven factors. This paper investigates a parametric modeling method for prediction of the development cost of general aviation aircraft. The proposed technique depends on some principal components, acquired by utilizing P value analysis and gray correlation analysis. According to these principal components, the corresponding linear regression and BP neural network models are established respectively. The feasibility and accuracy of the P value analysis are verified by comparing results of model fitting and prediction. A sensitivity analysis related to model precision and suitability is discussed in detail. Results obtained in this study show that the proposed method not only has a certain degree of versatility, but also provides a preliminary prediction of the development cost of general aviation aircraft. 相似文献
849.
850.
《中国航空学报》2020,33(10):2743-2756
Blisks with the integral structure are key parts used in new jet engines to promote the performance of aircrafts, which also increases the complexity of tool orientation planning in the five-axis machining. It is an essential task to find the collision-free tool orientation when the tool holder is pushed deep into the channel of blisk to increase rigidity and reduce vibration. Since the radius of the holder varies with the height, the line-visibility is no longer applicable when constructing collision-free regions of tool orientation. In this paper, a method of constructing collision-free regions without interference checking is proposed. The work of finding collision-free regions resorts to solving the local contact curves on the checking surfaces of blisk. And it further transforms into searching the locally tangent points (named critical points) between the holder and surface. Then a tracking-based algorithm is proposed to search the sample critical points on these local contact curves. And the corresponding critical vectors are also calculated synchronously. Besides, the safety allowance, discrete precision and acceptable deviation are introduced in the algorithm to ensure accuracy by controlling the angle between two adjacent critical vectors properly. After that, the searched critical vectors are mapped orderly to two-dimensional space and the collision-free regions are constructed. This method is finally verified and compared with a referenced method. The results show that the proposed method can efficiently construct collision-free regions for holder under the given accuracy. 相似文献