超声速降落伞系统的气动干扰数值模拟研究

发布时间：2018-06-20 08:24

本文选题：气动干扰分离 + 涡模拟　；参考：《航天返回与遥感》2016年03期

【摘要】：文章基于一种简易"浸入边界技术"与流固耦合方法对超声速来流条件下的三维降落伞系统进行了数值模拟。文章分析了降落伞系统(太空舱和降落伞衣)流场产生的气动干扰对伞衣外形变形动力学的影响以及降落伞设计参数(如拖拽距离参数)对降落伞性能表现的影响,同时检验了分离涡模拟方法在三维超声速降落伞数值模拟中的适用性。结果表明,当拖拽距离参数很小时,伞衣出现了严重的收缩现象;当距离增大时,观测到了伞开口的"呼吸现象",阻力系数获得了较大改善。另外,在拖拽距离参数较大的情况下,由于湍流尾流与伞前激波的气动干扰影响明显,采用分离涡模拟方法,可以获得较层流尾流条件下更大的阻力系数。
[Abstract]:Based on a simple "immersion boundary technique" and fluid-solid coupling method, a numerical simulation of a three-dimensional parachute system under supersonic flow is presented in this paper. In this paper, the influence of aerodynamic interference caused by the flow field of parachute system (capsule and parachute coat) on the shape deformation dynamics of parachute and the influence of parachute design parameters (such as drag distance parameter) on the performance of parachute are analyzed. At the same time, the applicability of the separation vortex simulation method in the numerical simulation of three dimensional supersonic parachute is tested. The results show that when the drag distance parameter is very small, there is a serious contraction phenomenon in the canopy coat, and when the distance increases, the "breathing phenomenon" of the umbrella opening is observed, and the resistance coefficient is greatly improved. In addition, when the drag distance parameter is large, the drag coefficient can be obtained by using the separation vortex simulation method because the aerodynamic interference between turbulent wake and umbrella front shock wave is obvious.
【作者单位】：中南大学航空航天学院;香港理工大学深圳研究院;
【分类号】：V445.23

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