舰载倾转旋翼机着舰流场及气动干扰特性数值计算研究  

Research on numerical calculation of aerodynamic interactions characteristic and landing flow field of shipboard tilt rotor aircraft

作　　者：杨永飞[1] 林永峰[1] 牛青峰 樊枫[1] YANG Yongfei;LIN Yongfeng;NIU Qingfeng;FAN Feng(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《飞行力学》2022年第1期34-40,共7页Flight Dynamics

基　　金：直升机旋翼动力学国家级重点实验室基金资助(JZX7Y201911SY004001)。

摘　　要：针对舰载倾转旋翼机甲板着舰时的气动干扰问题,开展了着舰流场及气动干扰特性数值计算研究。首先,采用CFD技术建立了基于滑移网格方法的舰船与倾转旋翼计算模型,并通过试飞及风洞试验结果对比,验证了计算方法的合理性。然后,进行了倾转旋翼机流场及舰机复合流场数值计算,研究了风向及气流速度对倾转旋翼机着舰气动干扰特性的影响规律。结果表明:来流风速越大,气流经机库陡壁下冲速度越高,导致旋翼有效迎角减小,旋翼拉力减小;全机滚转力矩受侧向气流干扰左侧升力增大时,引起向右的滚转力矩;全机俯仰力矩受气流偏角的影响,气流从前方流动产生抬头力矩,气流从后方流动产生低头力矩。Aiming at the problem of aerodynamic interference of tilt rotor aircraft landing on the ship deck, the numerical calculation research of the flow field of landing on the ship deck and aerodynamic interference characteristics were carried out. Firstly, the calculation model of ship and tilt rotor based on sliding grid method was established using CFD technology, and the results of flight test and wind tunnel test were compared to verify the rationality of the calculation method. Then, the numerical calculation of the flow field of the tilt rotor aircraft and the composite flow field of the ship and aircraft was carried out, and the influence law of wind direction and air velocity on the aerodynamic interference characteristics of the tilt rotor aircraft landing on the ship was studied. The results show that the higher the incoming wind speed, the higher the downward velocity of the airflow through the hangar’s steep wall, which leads to a decrease in the effective angle of attack of the rotor and a decrease in the thrust force of the rotor. The rolling moment of the whole aircraft is interfered by the sideways airflow when the lift force on the left increases, causing a rightward rolling moment. The pitch moment of the whole aircraft is interfered by the airflow deflection angle, the airflow flowing from ahead produces a head-up moment, and the airflow flowing from the rear produces a nose-down moment.

关 键 词：倾转旋翼机 舰载环境 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]