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排序方式: 共有151条查询结果,搜索用时 218 毫秒
101.
102.
基于MATLAB/Simulink平台,建立了某大型商用飞机的起落架模型。系统建立了起落架的减震支柱、轮胎侧向力、收放等模型,在此基础上能够实时模拟收放、前起落架转向、主起落架刹车等过程。结合验证数据进行比较证明,仿真结果合理,模型正确。将起落架模型集成到整个飞行实时仿真系统中进行实时仿真,可用于起落架相关的课程教学与研究中。 相似文献
103.
Heavy-equipment airdrop is a highly risky procedure that has a complicated system due to the secluded and complex nature of factors' coupling. As a result, it is difficult to study the modeling and safety simulation of this system. The dynamic model of the heavy-equipment airdrop is based on the Lagrange analytical mechanics, which has all the degrees of freedom and can accurately pinpoint the real-time coordinates and attitude of the carrier with its cargo. Unfavorable conditions accounted in the factors' models, including aircraft malfunctions and adverse environments, are established from a man-machine-environment perspective. Subsequently, a virtual simulation system for the safety research of the multi-factor coupling heavy-equipment airdrop is developed through MATLAB/Simulink, C language and Flightgear software. To verify the veracity of the theory, the verification model is built based on dynamic software ADAMS. Finally, the emulation is put to the test with the input of realistic accident variables to ascertain its feasibility and validity of this method. 相似文献
104.
运用基于工艺的“laminate modeler”模块创建了复合材料铺层和加筋层合板的三维有限元模型.介绍了一种体单元与壳单元节点融合的方法.以不同的相对节点间距对加筋层合板模型进行了有限元网格划分,采用结构最大Von Mises应力作为标准进行了收敛性分析,得到了一个可适用于其他类似加筋板模型网格创建的合理相对节点间距值1/72.应力计算表明,集中载荷作用下复合材料加筋壁板的初始损伤发生于第八铺层材料主方向的2方向,损伤模式为基体拉伸开裂.发生初始损伤时加筋板结构的极限载荷为75 N.应力集中区较小,且主要分布于载荷作用点附近.集中载荷作用下加筋板的承载效率较低. 相似文献
105.
106.
O.A. Maltseva N.S. MozhaevaT.V. Nikitenko 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
Empirical modeling including empirical model for the total electron content (TEC) is important for the study of the ionosphere and practical applications. In this paper goodness of new Neustrelitz Global Model (then NGM) at low latitudes is studied. The NGM model includes such parameters as the maximal electron density (NmF2) and altitude of the maximum (hmF2). As of today, besides NGM there are several empirical models for NmF2 and hmF2. Therefore, a comparison of these parameters of the NGM model, not only with the experimental data, but also with two versions of the International Reference Ionosphere (the IRI model): IRI2001 and IRI-Plas would be instructive. Because the NGM model incorporates special factor describing the equatorial anomaly, the comparison in lower latitude areas is particularly interesting. As one can see from the presented example of the data from low latitude stations located in the northern and southern hemispheres near the Greenwich meridian, the NGM model may have certain advantages over the IRI model versions. In particular, NGM TEC is preferable regardless of solar activity level while NGM NmF2 is only preferable under high solar activity conditions. Next, NGM equivalent slab thickness of the ionosphere: τ(NGM) = TEC(NGM)/NmF2(NGM) has been calculated and tested to answer the question whether τ(NGM) can be used as a proxy of the slab thickness of the ionosphere for an empirical modeling. The answer is positive for the near equatorial stations and periods of high solar activity, and under such conditions predicted τ(NGM) can be used for deriving NmF2 from the experimental values of TEC(CODE) in real time. 相似文献
107.
动能拦截器末制导控制系统建模与仿真 总被引:6,自引:1,他引:6
对动能拦截器末段拦截的制导与姿态控制系统进行建模和仿真分析。首先建立末制导系统模型,其中包括拦截器结构模型、六自由度动力学与运动学模型、测量模型和制导控制律模型。重点分析了拦截器质心位置误差和发动机推力偏心造成的推力和力矩误差,以及由此造成的轨控系统与姿控系统的相互影响。采用一种分段末制导律,并将基于相平面分析的方法用于姿态控制律设计,以克服干扰力矩的影响。仿真分析表明,采用相应的轨控和姿控方案,能保证系统的稳定性,对目标进行成功拦截。 相似文献
108.
管路系统敷设的并行工程模型研究 总被引:3,自引:0,他引:3
提出了一种应用于并行工程模型转换研究的标号法,该法是将现行串行设计过程(As-is)转换为并行设计过程(To-be)。本文应用该法将发动机外部管路系统敷设过程模型进行了串并行转换,应用并行工程过程重构的手段,得到了管路敷设并行过程模型,文中对该模型进行了详细分析。最后对转换前后的模型进行了时间效益分析,得到了对敷管工程有指导意义的结论。 相似文献
109.
110.
This paper illustrates the dynamic modeling, experimental validation of Reusable Launch Vehicle under symmetric landing mode. Firstly, a new quasi-3D dynamic landing model of vehicle under 2-2 and 1-2-1 symmetric landing mode is established, which can predict the plane motion of the main body and the spatial motion of landing struts and footpads. The strut force,footpad-ground contact force and the liquid spring damper are also included in the model. Secondly, the landing impact experiments are ... 相似文献