基于CFD与飞行动力学耦合方法的舰载直升机着舰平衡分析  

Balance Analysis of Shipboard Helicopter Landing by CFD and Flight Dynamics Coupling Model

作　　者：孟晓伟[1] 徐国华[1] 史勇杰[1] 黄斌[1] 

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,南京210016

出　　处：《南京航空航天大学学报》2016年第2期238-243,共6页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(11302103)资助项目;江苏高校优势学科建设工程资助项目

摘　　要：将计算流体力学(Computational fluid dynamics,CFD)模型与飞行动力学模型相结合,建立了适用于舰载直升机着舰飞行的平衡分析方法。在满足气动力计算精度的前提下,为提高计算效率,CFD模型使用Euler方程作为主控方程,并采用动量源项代替旋翼对其流场的作用。将CFD计算所得气动力对飞行动力学模型计算所得气动力进行修正迭代,并根据牛顿迭代法求解飞行动力学平衡方程,最终求得平衡参数。应用所建立的方法,首先进行了算例验证,以表明方法的有效性;然后着重对舰载直升机着舰飞行进行了平衡计算与分析,为直升机着舰飞行提供参考。A method for analyzing the balance of shipboard helicopter landing is established by combining CFD model with flight dynamics model. On the premise of meeting calculation requirement of aerody- namic forces, Euler equations are used as governing equations for CFD model to improve calculative effi- ciency, and the momentum-source term is used to describe the effects of rotor and tail rotor on its flow- field. Aerodynamic forces calculated by the flight dynamics model are corrected by forces calculated by the CFD model. Furthermore, according to the Newton iteration method, trim parameters are obtained by solving the flight dynamics trim equations. By show the effectiveness of the method. And then, is performed. the proposed method, a validation example is given to the balance calculation of shipboard helicopter landing

关 键 词：舰载直升机 动量源 CFD模型 飞行动力学模型 平衡 

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]