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通过理论研究以及高频仿真相结合的方法分析设计了一款新型Ka波段8路径向波导空间功率分配(合成)器。研发的新结构输入输出段为标准矩形波导结构,代替了传统功率分配(合成)器输入输出段的同轴结构,这种新型全金属结构更加简单紧凑,更易于加工。仿真结果表明:功率分配(合成)器工作带宽达到了34%(12GHz),基本覆盖整个Ka波段;全频带内反射系数S11低于-20dB,各支路的相位差均小于5°。通过在同轴波导渐变段引入切比雪夫渐变结构,在减小了器件尺寸的同时,在整个频带内的网络S参数也不错。这款新型Ka波段8路径向波导功率分配(合成)器将应用于前级固态功率放大器,推动回旋行波管项目研发。 相似文献
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Graphene-based heterostructure is one of the most attractive topics in physics and material sciences due to its intriguing properties and applications. We report the one-step fabrication of a novel graphene/Mo_2C heterostructure by using chemical vapor deposition(CVD). The composition and structure of the heterostructure are characterized through energydispersive spectrometer, transmission electron microscope, and Raman spectrum. The growth rule analysis of the results shows the flow rate of methane is a main factor in preparing the graphene/Mo_2C heterostructure. A schematic diagram of the growth process is also established. Transport measurements are performed to study the superconductivity of the heterostructure which has potential applications in superconducting devices. 相似文献
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Effects of tip perturbation and wing locations on rolling oscillation induced by forebody vortices 总被引:1,自引:0,他引:1 下载免费PDF全文
The wing rock motion is frequently suffered by a wing-body configuration with low swept wing at high angle of attack. It is found from our experimental study that the tip perturbation and wing longitudinal locations affect significantly the wing rock motion of a wing-body. The natural tip perturbation would make the wing rock motion of a nondeterministic nature and an artificial mini-tip perturbation would make the wing rock motion deterministic. The artificial tip perturbation would, as its circumferential location is varied, generate three different types of motion patterns: (1) limit cycle oscillation, (2) irregular oscillation, (3) equilibrium state with tiny oscillation. The amplitude of rolling oscillation corresponding to the limit cycle oscillatory motion pattern is decreased with the wing location shifting downstream along the body axis. 相似文献
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利用壁面压力测量和表面油流显示技术对后掠压缩角产生的激波与湍流边界层干扰进行了实验研究。主要研究了来流马赫数对干扰分离特性和起始分离条件的影响,实验的马赫数为1.79,2.04和2.50,相应的雷诺数为2.42—2.47×10 ̄7/m.实验模型共15个,其后掠角变化范围是0°—60°,流向压缩角变化范围是10°—30°,实验结果表明,与二维干扰不同,对于大后掠角的三维干扰来说,分离线上的压比和起始分离时的无粘激波压比近似相等,且是一个与马赫数无关的常数。 相似文献
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大迎角细长体绕流背涡结构与气动特性分析 总被引:5,自引:0,他引:5
结合实验成果,对大迎角细长体绕流结构及其气动特征进行了分析。利用势流理论,探讨了大迎角下非对称侧向力沿物体轴线的变化特征与分离背涡结构之间的关系,得出截面侧向力系数沿轴向呈现正弦型曲线的变化特征是由轴向旋涡不断脱落所形成的多涡系统诱导的结果。对于三涡以上的多涡系统中,对称的物面压强分布并非一定对应对称的涡结构。 相似文献
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Asymmetric vortices flow over slender body and its active control at high angle of attack 总被引:5,自引:0,他引:5
The studies of asymmetric vortices flow over slender body and its active control at high angles of attack have significant
importance for both academic field and engineering area. This paper attempts to provide an update state of art to the investigations
on the fields of forebody asymmetric vortices. This review emphasizes the correlation between micro-perturbation on the model
nose and its response and evolution behaviors of the asymmetric vortices. The critical issues are discussed, which include
the formation and evolution mechanism of asymmetric multi-vortices; main behaviors of asymmetric vortices flow including its
deterministic feature and vortices flow structure; the evolution and development of asymmetric vortices under the perturbation
on the model nose; forebody vortex active control especially discussed micro-perturbation active control concept and technique
in more detail. However present understanding in this area is still very limited and this paper tries to identify the key
unknown problems in the concluding remarks.
The project supported by the National Natural Science Foundation of China (10172017), Aeronautical Science Foundation of China
(02A51048) and Foundation of National Key Laboratory of Aerodynamic Design and Research (51462020504HK0101) 相似文献