摘要
针对双机身布局飞机在气动和飞行力学方面的特殊性,采用CFD数值方法计算并分析了双机身、双垂尾布局验证机的气动特性,基于飞行动力学理论分析了其横航向飞行品质特性。结果表明:验证机由于内外翼段失速迎角的差异,气动特性存在一定的非线性;验证机的横航向典型模态中螺旋模态稳定,荷兰滚模态和滚转模态在高空低速时只能满足2级飞行品质标准,荷兰滚阻尼比具有随巡航速度增加而增加的特点,副翼能力略显不足;飞行高度和飞行重量增加会降低横航向稳定性。
In order to study the particularity of bi-fuselage aircraft in aerodynamic and flight mechanics,the aerodynamic characteristics of the demonstrator with double fuselage and double vertical tail layout were calculated and analyzed by CFD numerical method,and the transverse and directional flight quality characteristics were analyzed based on flight dynamics theory.The results show that the aerodynamic characteristics of the aircraft tend to be nonlinear due to the difference of the stall angle of attack between inner and outer wings.The spiral mode is stable and the Dutch roll mode and roll mode can only meet the level 2 flight quality standard at high altitude and low speed.The Dutch roll damping ratio increases with the increase of cruise speed,and the aileron capability is slightly insufficient.The increase of flight altitude and weight will reduce the lateral and directional stability of the aircraft.
作者
艾梦琪
郭保
赵彦
AI Mengqi;GUO Bao;ZHAO Yan(AVIC The First Aircraft Institute,Xi'an 710089,China;95885 Troops of the PLA,Xi'an 710089,China)
出处
《飞行力学》
CSCD
北大核心
2023年第6期10-15,共6页
Flight Dynamics
关键词
双机身布局
飞行动力学
气动特性
飞行品质
bi-fuselage layout
flight dynamics
aerodynamic characteristics
flight qualities
