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71.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(7):1852-1862
This work reviews and expands upon the previous fluorination processes for in situ production of oxygen and silicon from lunar regolith. The process units were simulated and a flow sheet was developed to determine the product distribution and energy requirements. Our results show that 0.21 kg silicon and 0.32 kg oxygen can be produced per kg regolith processed with a total cooling duty of 17 MJ/kg regolith and electrical duty of 29 MJ/kg regolith. The payload mass required for the process is estimated as 16 kg/kg regolith processed per day. 相似文献
72.
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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航班地面保障是机场运行的重要环节,为了提升航班地面保障效率,针对某机场航班地面保障流程构建AOE 网,通过该机场A-CDM 系统记录的航班节点数据求出该机场航班地面保障作业的“关键路径”。通过对关键路径上可压缩工序的分析,对该机场的地面保障作业流程进行优化。以我国西南地区某机场航班地面保障的实际数据为基础,剔除不可抗力造成的不正常数据,分别计算保障流程优化前后的航班过站时间。结果表明:在33 组航班数据中,该机场使用AOE 网络优化后的保障作业流程比优化前平均减少地面保障作业时长6.1 分钟/架次,说明通过合理地优化航班地面保障进程,可以有效提高机场的运行效率。 相似文献
75.
机器人取代机床从事机械加工已成为自动化加工发展的一大趋向。本文在分析工业机器人应用现状的基础上,提出了机器人加工系统存在的一些问题,还对并联机床的发展作了展望。 相似文献
76.
A block-structured adaptive mesh refinement (AMR) method was applied to the computational problem of acoustic radiation from an aeroengine intake. The aim is to improve the computational and storage efficiency in aeroengine noise prediction through reduction of computational cells. A parallel implementation of the adaptive mesh refinement algorithm was achieved using message passing interface. It combined a range of 2nd- and 4th-order spatial stencils, a 4th-order low-dissipation and low-dispersion Runge–Kutta scheme for time integration and several different interpolation methods. Both the parallel AMR algorithms and numerical issues were introduced briefly in this work. To solve the problem of acoustic radiation from an aeroengine intake, the code was extended to support body-fitted grid structures. The problem of acoustic radiation was solved with linearised Euler equations. The AMR results were compared with the previous results computed on a uniformly fine mesh to demonstrate the accuracy and the efficiency of the current AMR strategy. As the computational load of the whole adaptively refined mesh has to be balanced between nodes on-line, the parallel performance of the existing code deteriorates along with the increase of processors due to the expensive inter-nodes memory communication costs. The potential solution was suggested in the end. 相似文献
77.
Peter M.B. Waswa Michael ElliotJeffrey A. Hoffman 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Space missions designed to completely ablate upon an uncontrolled Earth atmosphere reentry are likely to be simpler and cheaper than those designed to execute controlled reentry. This is because mission risk (unavailability) stemming from controlled reentry subsystem failure(s) is essentially eliminated. NASA has not customarily implemented Design-for-Demise meticulously. NASA has rather approached Design-for-Demise in an ad hoc manner that fails to entrench Design-for-Demise as a mission design driver. Thus, enormous demisability challenges at later formulation stages of missions aspired to be demisable are evident due to these perpetuated oversights in entrenching Design-for-Demise practices. The investigators hence propose a strategy for a consistent integration of Design-for-Demise practices in all phases of a space mission lifecycle. Secondly, an all-inclusive risk-informed, decision-making methodology referred to as Analytic Deliberative Process is proposed. This criterion facilitates in making a choice between an uncontrolled reentry demisable or controlled reentry. The authors finally conceive and synthesize Objectives Hierarchy, Attributes, and Quantitative Performance Measures of the Analytical Deliberative Process for a Design-for-Demise risk-informed decision-making process. 相似文献
78.
为了给各保险公司进行商场建筑的承保和费率的确定提供参考,并克服保险人在确定费率时的主观性,应用层次分析和火灾风险调查表的方法,对商场建筑的火灾危险性进行评价,确定商场建筑的火灾危险等级,据此确定保险费率应如何浮动。当保险的赔偿限额小于500万元时,对于火灾危险等级为Ⅰ、Ⅱ、Ⅲ、Ⅳ、Ⅴ级的商场,保险费率相对标准费率分别上调20%、上调10%、不变、下调10%和下调20%;当保险的赔偿限额大于500万元时,对于火灾危险等级为Ⅱ、Ⅲ、Ⅳ、Ⅴ级的商场,保险费率相对标准费率分别上调15%、上调10%、不变和下调10%,对于火灾危险等级为Ⅰ级的商场拒绝承保。 相似文献
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The isothermal local loading forming technology provides a feasible way to form Ti-alloy large-scale rib-web components in aerospace and aviation fields.However,the local load ing process forming limit is restricted by forming defects in the transitional region.In this work,the feasibility of controlling forming defects and improving the process forming limit by adjusting die parameters is explored through finite element (FE) simulation.It is found that the common cavum and folding defects in the transitional region are significantly influenced by the fillet radii of left rib and middle rib,respectively.The cavum and folding defects can be effectively controlled by increas ing the fillet radii of left rib and middle rib,respectively.The process forming limits considering forming defects in the transitional region are determined by the stepwise searching method under various die parameters.Moreover,the relationship between the process forming limit and die parameters is developed through the response surface methodology (RSM).The developed RSM models suggest that increasing the fillet radii of left and middle ribs is effective to improve the pro cess forming limit during local loading forming of rib-web components.The results will provide technical basis for the design of die parameters and the reduction amount,which is of great impor tance to control forming defects and improve the process forming limit in local loading forming of Ti-alloy large-scale rib-web components. 相似文献