摘要
针对空投系统以及航天器回收过程中的翼伞,采用计算流体动力学法对翼伞气动性能进行研究,通过数值仿真获取翼伞气动参数及参数变化规律,并与传统风洞试验法进行比较,对比结果说明了数值仿真所获参数的准确性,验证了计算流体动力学法对翼伞气动性能研究的可行性,并克服了风洞试验法在翼伞气动性能测试中受伞衣规模尺寸的约束问题。
For the air-drop system and spacecraft recovery system,the aerodynamic performances of the parachute were studied with the method of the Computational Fluid Dynamics,with the aerodynamic parameters and the variation of aerodynamic parameters obtained by numerical simulation,which was compared with the traditional wind tunnel test method.The comparison results show the accuracy of the parameters obtained by numerical simulation,verify the feasibility of the Computational Fluid Dynamics method to study the aerodynamic performances of the parachute,and solve the problem that the wind tunnel test method is constrained by the size of the parachute.
作者
李艳红
张小青
李雅静
LI Yanhong;ZHANG Xiaoqing;LI Yajing(School of Physics and Electrical Engineering,Xianyang Normal University,Xianyang 712000,Shaanxi,China)
出处
《咸阳师范学院学报》
2019年第6期47-50,共4页
Journal of Xianyang Normal University
基金
咸阳师范学院科研基金项目(XSYK18048)
关键词
计算流体动力学
翼伞
风洞试验
气动性能
computational fluid dynamics
parachute
wind tunnel test
aerodynamic performance
