倾转翼飞机悬停时俯仰姿态的气动控制

Aerodynamic Control of the Pitch Attitude of the Tilt Rotor in Hovering

提出一种新的倾转翼飞机悬停时俯仰控制方式,即通过安装有电机的外端机翼和其正下方的副翼均按同为顺时针或同为逆时针侧偏转的方式来控制飞机悬停时的俯仰姿态及前后运动,发现需要倾转的外端机翼和副翼不但要满足平飞时的气动特性,同时也要满足悬停时的气动及力矩要求,以及安装在外端机翼上的副翼偏转角度对悬停俯仰姿态控制要求。本文首先采用NACA23012翼型,在CATIA建立几何模型并在ICEM中生成非结构化网格,并应用Fluent软件计算得到悬停时旋转段机翼和副翼的气动特性,分析了悬停时对俯仰力矩的要求,根据计算结果进一步修改翼型得到满足设计要求的方案。

A new kind of rotated wing aircraft in hover pitch control mode was presented to ensure the stability of aircraft through its outer end of the rotary wing and aileron linkage. It is necessary to tilt the outer end of the wing and aileron to meet not only the aerodynamic characteristics of level flight but also the pneumatic and torque requirements when hovering,and meet the deflection angle of aileron which was installed in its outer end of the rotary wing to the hover pitch control requirements. Firstly,the NACA23012 airfoil is used to build the geometric model in CATIA and the unstructured mesh is generated in ICEM,then aerodynamic characteristics of the rotary wing and aileron when hovering was calculated by using Fluent,and analyzed the requirement of torque in hover,then,based on the calculation results,further modified airfoils satisfy the design requirements of the scheme.