冲压式翼伞气动性能研究  

Research on aerodynamic performance of ram-air parafoil

作　　者：刘媛[1] 闫建国[1] 李明君[1] 屈耀红[1] 

机构地区：[1]西北工业大学自动化学院,陕西西安710129

出　　处：《飞行力学》2017年第3期24-27,36,共5页Flight Dynamics

基　　金：国家自然科学基金资助(60974146;61473229);西北工业大学研究生创意创新种子基金资助(Z2016148)

摘　　要：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。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 3 D parafoil. Firstly, the finite volume method was used to solve the N-S control e- quation of K-8 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 mod- eling of parafoil, thus overcoming the shortcomings of the inaccurate aerodynamic parameters got with the traditional empirical formulas.

关 键 词：气动性能 后缘下偏 气动参数 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]