摘要
针对倾转四旋翼飞行器,采用计算流体力学(computational fluid dynamic,CFD)方法建立了其倾转过渡状态的全机数值计算模型,可用于其气动特性的计算与分析。首先,基于动量源方法建立旋翼气动分析模型,对孤立旋翼进行气动计算并与实验结果进行对比,验证动量源方法的有效性;然后,建立全机的气动干扰数值计算模型,其中使用动量源代替旋翼并划分结构网格,对机身/机翼/短舱则采用非结构化网格进行划分;最后,分析该倾转四旋翼飞行器倾转过渡状态下旋翼与机翼的气动干扰特性,得到旋翼/机翼的气动干扰规律,可以支撑飞行器总体设计。
A numerical simulation model is established by CFD method for quad tilt rotor aircraft in conversion state. The method can be used to calculate and analyze the aerodynamic characteristics. Firstly, based on the momentum source method, the lift force and power of the isolated rotor are calculated and compared with the experimental results, and the effectiveness of the momentum source method is verified. Then the aerodynamic interference calculation model of the whole aircraft is established, in which the rotors are represented by momentum source and divided by structured grids, and the unstructured grids are applied to the fuselage, wings and nacelles. Finally, the aerodynamic interference characteristics of the rotors and the wings in conversion state are analyzed, some aerodynamic interference laws are obtained and the aircraft overall design is supported.
作者
陈天予
徐逸
梁壮
王皓
CHEN Tianyu;XU Yi;LIANG Zhuang;WANG Hao(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)
出处
《空天防御》
2020年第1期17-22,共6页
Air & Space Defense
关键词
动量源
倾转四旋翼
过渡状态
干扰特性
总体设计
momentum-source
quad tilt rotor
conversion state
interference characteristics
overall design
