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作 者:刘夏真 袁武[1] 李齐[3] 赵瑞[4] 张鉴[1] 陆忠华[1] Liu Xiazhen;Yuan Wu;Li Qi;Zhao Rui;Zhang Jian;Lu Zhonghua(Computer Network Infbrmation Center,Chinese Academy of Sciences,Beijing 100190,China;University of Chinese Academy of Sciences,Beijing 100049,China;Institute of Spacecraft System Engineering,Beijing 100094,China;School of Aerospace Engineering,Beijing institute of technology,Beijing 100081,China)
机构地区:[1]中国科学院计算机网络信息中心,北京100190 [2]中国科学院大学,北京100049 [3]北京空间飞行器总体设计部,北京100094 [4]北京理工大学宇航学院,北京100081
出 处:《系统仿真学报》2021年第7期1582-1590,共9页Journal of System Simulation
基 金:国家重点研发计划(2019YFB1704202);国家自然科学基金(11871454,11902025,61702438);中国科学院战略性先导科技专项(XDB22020102,XDC01040100);中国科学院信息化专项(XXH13506-204)。
摘 要:降低激波阻力是火星上升器气动优化的重要目标。采用计算流体力学(Computational Fluid Dynamics, CFD)方法,针对典型短钝锥上升器外形的超声速阻力特性开展研究,在长细比0.42的设计约束下,比较了13组母线外形的零升阻力,并讨论了纵向静、动稳定性。研究表明:在设计约束下,球鼻大且锥面平缓的钝头形状有低阻特性,原因是超声速气流在经过球鼻后连续膨胀减压,形成了球鼻处小范围的高压区和锥面处大范围的低压区,使整体阻力下降;短钝锥外形有较高静稳定性和呈现临界动稳定性。Reducing shock drag is an important objective of the aerodynamic optimization of Mars ascenders. The CFD(Computational Fluid Dynamics) method is used to study the supersonic drag characteristics of a typical blunt cone ascender. Under the design constraints of slenderness ratio of 0.42, 13 groups busbar shape set of zero-lift drag are compared, and the longitudinal static and dynamic stability are discussed. The research results show that, under the design constraints, the blunt shape with large bulbous and a gently sloped conical surface has low drag characteristics. The reason is that, after passing through the bulbous, the supersonic airflow is continuously expanded and depressurized, and are formed a small area of high pressure at the bulbous nose and a large area of low pressure at the cone surface, which reduce the overall drag. Moreover, the shape of blunt cone has higher static stability and critical dynamic stability.
分 类 号:TP391.9[自动化与计算机技术—计算机应用技术]
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