排序方式: 共有58条查询结果,搜索用时 15 毫秒
51.
Stratospheric airship is a special near-space air vehicle, and has more advantages than other air vehicles, such as long endurance, strong survival ability, excellent resolution, low cost, and so on, which make it an ideal stratospheric platform. It is of great significance to choose a rea-sonable and effective way to launch a stratospheric airship to the space for both academic research and engineering applications. In this paper, the non-forming launch way is studied and the method of differential pressure gradient is used to study the change rules of the airship's envelope shape dur-ing the ascent process. Numerical simulation results show that the head of the envelope will main-tain the inflatable shape and the envelope under the zero-pressure level will be compressed into a wide range of wrinkles during the ascent process. The airship's envelope will expand with the ascent of the airship and the position of the zero-pressure level will move downward constantly. At the same time, the envelope will gradually form a certain degree of stiffness under the action of the inner and external differential pressure. The experimental results agree well with the analytical results, which shows that the non-forming launch way is effective and reliable, and the analytical method has exactness and feasibility. 相似文献
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利用2008年12月至2009年4月的MERRA再分析数据资料,对2009年1月下旬北半球高纬平流层发生的强增温事件以及与之相关的行星波活动进行了研究.谱分析发现,SSW发生前后极区平流层内准16天行星波活动显著.利用二维谐波拟合法分别拟合温度场准16天波4个波模(W1,W2,E1,E2)的振幅和相位,结果表明:背景西风减弱时四个波模的振幅均有不同程度的增大,且都在50°-80°N范围内的平流层中上层达到最大值;准16天W2波的增幅最大且辐合最强烈,其引起的背景流最大西风减速超过4m·-1·d-1,说明准16天W2波在该次增温事件中占主导地位;行星波传播与零风线移动关系密切,准16天W2波在中高纬地区垂直向上传播并近似呈现经向驻波结构,然后分别向极点和赤道两个方向传播,这表明中高纬地区可能是行星波的一个源区. 相似文献
53.
文章从介绍平流层飞艇的结构健康监测定义入手,说明了该系统研究的作用和意义以及工作原理。在分析平流层飞艇运行环境和结构可能的损伤模式的基础上,从工程应用角度出发,对结构健康监测系统方案展开了研究,探讨了平流层飞艇结构健康监测系统中的一些关键因素,为今后结构健康监测系统设计提供参考。 相似文献
54.
平流层飞艇外形气动特性分析 总被引:1,自引:0,他引:1
结合某平流层飞艇的外形设计,文章采用数值模拟的方法研究了平流层飞艇外形的气动特性。基于雷诺平均N—S方程,采用非结构网格的有限体积方法进行了求解;空间离散分别采用了Jameson的中心格式和Osher逆风格式,时间离散则采用五步Runge—Kutta格式;紊流模型分别采用了S—A一方程模型M—SST两方程模型。本研究有助于了解平流层飞艇的气动特性及气动外形设计过程中存在的问题,为平流层飞艇设计提供参考依据。 相似文献
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56.
L.K. Amekudzi A. Bracher K. Bramstedt A. Rozanov H. Bovensmann J.P. Burrows 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008,41(11):1921-1932
Vertical profiles of stratospheric nitrogen dioxide (NO2) have been retrieved from moderate resolution lunar occultation transmission spectra measured by Scanning Imaging Absorption spectroMeter for Atmospheric CHartographY (SCIAMACHY) on board the European Environmental Satellite (ENVISAT). These measurements were taken over the high southern latitude of 50°–90° during the period of 2003–2005. To assess the accuracy of the retrieved NO2 profiles, the SCIAMACHY nighttime NO2 profiles were compared with NO2 profiles retrieved from sunrise solar occultation spectra measured by the Halogen Occultation Experiment (HALOE) and the Stratospheric Aerosol and Gas Experiments II (SAGE II) using a photochemical correction model. The validation results show good agreement of SCIAMACHY lunar occultation NO2 with scaled HALOE and SAGE II profiles. The relative mean differences (rmd) with scaled HALOE profiles are within −13% to +5% and standard deviations (rms) of the relative differences are within 3–19% between 25 and 38 km. The rmd and rms with scaled SAGE II NO2 profiles are in the range of −9 to +7 and 10–17% respectively between 22 and 39 km. 相似文献
57.
针对平流层飞艇蒙皮材料初始损伤对于其撕裂破坏的影响,分析了国内外现阶段研究柔性层压织物材料双向撕裂扩展的四种方法及对应的经验公式,通过与某平流层飞艇蒙皮材料双轴向拉伸实验得出的试验结果比较,得出各个方法的优缺点及其应用范围,并指出泰勒公式对于蒙皮材料撕裂性能的研究较为适用。同时,针对不同初始损伤切口形状的蒙皮材料进行试验值与经验公式的对比,指出不同初始损伤切口形状可等效为切断同等尺寸的经向纱线所产生的影响,并分析了蒙皮材料撕裂强度的主要影响因素,对平流层飞艇高性能蒙皮材料撕裂性能的研究提供参考。 相似文献
58.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(6):2702-2710
The European Stratospheric Balloon Observatory (ESBO) initiative aims at simplifying the access to stratospheric balloon missions. We plan to provide platforms and support with instrument design in order to support scientists. During the design process, the inevitable question of qualification for the harsh flight conditions arises. Unfortunately, there is no existing standard for qualification of stratospheric ballooning hardware. Thus, we developed a qualification procedure for use within ESBO and similar projects.In this paper, we present our analysis of the environmental conditions in the stratosphere. While conditions at typical balloon float altitudes are similar to the space environment, there are also some relevant differences. For example, the thermal environment is dominated by radiation and thermal conduction, but the remaining atmosphere still supports a certain amount of convection. The remaining atmospheric pressure in the stratosphere also leads to reduced arcing distances. Vibrational loads are far less than for space missions, but quasi-static or shock loads may occur. The criticality of radiation increases with mission duration.Based on the environmental conditions, we present the qualification procedures for ESBO, which are based on the European Cooperation for Space Standardization (ECSS) standards for space systems. Overtesting against too high requirements leads to overengineering, driving mission cost and mitigating the advantages of balloons over space missions. Therefore, we modified the ECSS standards to fit typical scientific ballooning missions over several days at altitudes up to 40 km. Furthermore, we analyzed design rules for space systems with regard to their relevance for scientific ballooning, including material and component selection. We present the experience from the hardware qualification process for the ESBO prototype STUDIO (Stratospheric UV Demonstrator of an Imaging Observatory). Even though boundary conditions are different for each individual mission, we aimed for a broader approach: We investigated more general requirements for scientific ballooning missions to support future flights. 相似文献