冲压式翼伞气动性能研究

随着计算流体动力学(CFD)的发展、空投系统以及航天器回收过程对定点回收精度要求的提高,精确计算冲压式翼伞的气动参数必不可少。首先,采用有限体积元法求解N-S湍流模型的κ-ε控制方程,对NASA兰利研究中心采用的三维翼伞进行了气动性能分析,验证了方法的可行性;然后将该方法应用于某型翼伞中,分析了翼伞周围的绕流特性,得到了不同迎角来流条件以及伞衣后缘不同程度下偏的气动力数据,为翼伞系统的数学建模提供了准确的参数,从而克服了传统经验公式获得气动参数不准确的缺点。

Research on aerodynamic performance of ram-air parafoil

With the development of CFD and improving request of accuracy in airdrop system and the process of spacecraft recovery, it is essential to conduct accurately calculate the aerodynamic coefficient based on the designed 3D parafoil.Firstly, the finite volume method was used to solve the N-S control equation of κ-ε model, analyze the performances of 3D parafoil used by NASA Langley research center, which validated the feasibility of the method.Then, the same method was applied to a parafoil, the flow field around the parafoil was analyzed, and the aerodynamic coefficients at different AOAs and different deflection of trailing edge of the canopy were obtained, which provide accurate data for mathematic modeling of parafoil, thus overcoming the shortcomings of the inaccurate aerodynamic parameters got with the traditional empirical formulas.