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961.
高轨卫星导航接收机是实现高轨航天器自主定轨的核心设备。为在地面测试阶段对高轨卫星导航接收机进行充分高效的验证,亟需设计基于高轨卫星导航接收机的地面测试系统。设计了一种基于高轨卫星导航接收机的自动化地面测试系统,主要创新点如下:第一,本系统可对高轨卫星导航接收机实际在轨状态下接收到的导航星座信号进行仿真;第二,具有模拟包含北斗三号等多导航卫星星座信号的功能;第三,本系统充分考虑自动化、通用化与一体化设计。提出的基于高轨卫星导航接收机的自动化地面测试系统能够在地面测试阶段对高轨卫星导航接收机进行充分验证,并充分考虑测试实施,从自动化、通用化、一体化方面提升测试效率,减少人为操作失误导致的质量问题,解决人工判读带来的误判漏判问题。 相似文献
962.
963.
《中国航空学报》2022,35(11):336-348
With the explosion of the number of meteoroid/orbital debris in terrestrial space in recent years, the detection environment of spacecraft becomes more complex. This phenomenon causes most current detection methods based on machine learning intractable to break through the two difficulties of solving scale transformation problem of the targets in image and accelerating detection rate of high-resolution images. To overcome the two challenges, we propose a novel non-cooperative target detection method using the framework of deep convolutional neural network.Firstly, a specific spacecraft simulation dataset using over one thousand images to train and test our detection model is built. The deep separable convolution structure is applied and combined with the residual network module to improve the network’s backbone. To count the different shapes of the spacecrafts in the dataset, a particular prior-box generation method based on K-means cluster algorithm is designed for each detection head with different scales. Finally, a comprehensive loss function is presented considering category confidence, box parameters, as well as box confidence. The experimental results verify that the proposed method has strong robustness against varying degrees of luminance change, and can suppress the interference caused by Gaussian noise and background complexity. The mean accuracy precision of our proposed method reaches 93.28%, and the global loss value is 13.252. The comparative experiment results show that under the same epoch and batchsize, the speed of our method is compressed by about 20% in comparison of YOLOv3, the detection accuracy is increased by about 12%, and the size of the model is reduced by nearly 50%. 相似文献
964.
针对高温压力传感器有引线封装在恶劣环境下的弊端,本文对无引线封装进行研究。首先,对无引线封装结构进行设计,并明确了适用无引线封装的高温压力敏感芯片结构;其次,研究了耐高温低应力气密封装工艺、低应力黏片工艺、无引线电气互联工艺,并实现工艺兼容。最后,将该无引线封装结构应用于高温压力敏感芯片,评估无引线封装效果。经测试,无引线封装结构漏率为10E-8 Pa·L/s,工作温度达300 ℃。本文的研究将拓展高温压力传感器应用领域,提高传感器恶劣环境的适应性及可靠性。 相似文献
965.
《中国航空学报》2023,36(1):22-44
Bird-like flapping-wing vehicles with a high aspect ratio have the potential to fulfill missions given to micro air vehicles, such as high-altitude reconnaissance, surveillance, rescue, and bird group guidance, due to their good loading and long endurance capacities. Biologists and aeronautical researchers have explored the mystery of avian flight and made efforts to reproduce flapping flight in bioinspired aircraft for decades. However, the cognitive depth from theory to practice is still very limited. The mechanism of generating sufficient lift and thrust during avian flight is still not fully understood. Moving wings with unique biological structures such as feathers make modeling, simulation, experimentation, and analysis much more difficult. This paper reviews the research progress on bird-like flapping wings from flight mechanisms to modeling. Commonly used numerical computing methods are briefly compared. The aeroelastic problems are also highlighted. The results of the investigation show that a leading-edge vortex can be found during avian flight. Its induction and maintenance may have a close relationship with wing configuration, kinematics and deformation. The present models of flapping wings are mainly two-dimensional airfoils or three-dimensional single root-jointed geometric plates, which still exhibit large differences from real bird wings. Aeroelasticity is encouraged to consider the nonignorable effect on aerodynamic performance due to large-scale nonlinear deformation. Introducing appropriate flexibility can improve the peak values and efficiencies of lift and thrust, but the detailed conclusions always have strong background dependence. 相似文献
966.
介绍在CAAA的FD04电孤风洞上进行的翼前缘防热材料烧蚀试验结果.试验模型由高温陶瓷制成,后掠角53°,高75 mm,长55 mm,前缘半径2 mm,对称截面半锥角为5°.试验设备包括20 MW电弧加热器、混合室、矩形超声速喷管、试验段、轨道模拟系统及真空系统等.使用的矩形超声速喷管的马赫数为3.6,以3个台阶的轨道模拟翼前缘热环境,试验时间为77.0 s.试验结果表明高温陶瓷具有优良的抗烧蚀性能,两件试验模型在试验过程中均未出现破损现象,试验还得到了翼前缘模型试验过程中的内部温度响应. 相似文献
967.
基于SAN构建高可用实时存储系统 总被引:1,自引:0,他引:1
介绍SAN网络存储技术及其拓扑结构,针对某飞控中心数据存储系统的实际需求,设计和实现一个SAN存储结构上的高可用实时可扩展集群存储方案,并详细描述通过软、硬件结合实现冗余数据路径、故障切换、实时存储和查询的方法。 相似文献
968.
969.
为了研究铺层区域变量对大展弦比机翼静气动弹性的影响,本文在考虑几何非线性影响下,依据有限元分析,研究了外翼段铺层区域的划分以及90°铺层角度的个数对大展弦比机翼静气动弹性特性的影响。结果表明,0°、±45°、90°混合铺层的铺设效果优于只有0°、±45°铺层的区域;机翼变形情况随着外翼段铺层区域的增大而减小,且减小斜率逐步增大;外翼段铺层区域固定时,增加90°铺层角度个数会有效减小机翼变形,且机翼变形情况与增加的个数基本呈现负相关关系,其个数在铺层设计中可能存在一个最佳取值或最优占比。 相似文献
970.