基于非定常动量源方法的全机耦合气动分析  

Coupled aerodynamic analysis of the whole helicopter based on unsteady momentum source method

作　　者：田晨浩 徐国华[1] 史勇杰[1] TIAN Chenhao;XU Guohua;SHI Yongjie(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《飞行力学》2022年第1期26-33,共8页Flight Dynamics

基　　金：江苏高校优势学科建设工程资助项目。

摘　　要：基于非定常动量源方法开展了直升机全机耦合气动分析研究。首先,以定常动量源模型为基础给出了高效的求解方法并验证其准确性。然后,将动量源项随时间变化添加至虚拟桨叶的所在位置,建立了能够体现流场非定常特性的非定常动量源模型。在此基础上,应用所建立的模拟方法深入开展了直升机全机耦合气动计算与分析。最后,结合飞行平衡模型分析了飞行参数对直升机气动特性的影响。研究结果表明,所建立的非定常动量源方法可以准确地模拟出桨叶的涡尾迹,可用于直升机全机耦合的气动分析研究。Based on the unsteady momentum source method, the whole aircraft coupling aerodynamic analysis of helicopter was carried out. Firstly, based on the steady momentum source model, an efficient solution method was given and its accuracy was verified. Then, the momentum source term was added to the position of the virtual blade with time, and an unsteady momentum source model which can reflect the unsteady characteristics of the flow field was established. On this basis, the whole aircraft coupling aerodynamic calculation and analysis of helicopter were carried out by using the established simulation method. Finally, combined with the flight balance model, the influence of flight parameters on the aerodynamic characteristics of helicopter was analyzed. The results show that the unsteady momentum source method can accurately simulate the vortex wake of the blade and can be used for the aerodynamic analysis of the whole helicopter coupling.

关 键 词：非定常 动量源 全机耦合 计算流体力学 气动干扰 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]