飞翼布局折叠机翼变体飞机操稳特性研究  

Study on controllability and stability of flying wing and folding wing morphing aircraft

作　　者：尹文强[1] 安然[1] 安玉娇[1] 

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089

出　　处：《飞行力学》2015年第6期495-499,共5页Flight Dynamics

摘　　要：为了研究飞翼布局折叠机翼变体飞机的操稳特性,自行设计飞翼布局折叠机翼变体飞机,建立研究模型并进行简化处理。采用涡格法和工程估算法对机翼折叠过程中飞机的纵向和横航向静稳定性进行分析;采用小扰动假设,将飞机扰动运动沿纵向和横航向解耦,分别得到纵向扰动运动和横航向扰动运动对应的模态,分析机翼折叠过程对飞机动稳定性的影响;结合工程估算法和CFD仿真分析机翼折叠过程对飞机操纵性的影响。飞行试验结果表明:在飞行中机翼折叠后,飞机有进入俯冲的趋势,随着配平舵偏角的增加,俯仰运动逐渐不够灵敏;在操纵杆量相同的情况下,机翼折叠状态的俯仰运动响应较快。To study the controllability and stability of flying wing and folding wing morphing aircraft,the aircraft was self-designed; the model was established and simplified. The longitudinal and lateral-directional static stability during the wings folding process of the aircraft were analyzed with vortex lattice method and the engineering estimation method. Using the small perturbation hypothesis,the aircraft perturbation motion were decoupled along the longitudinal and lateral-directional,and the corresponding modality of longitudinal perturbation motion and transverse heading perturbation motion were obtained. The effects on the dynamic stability of the aircraft during the wings folding process were analyzed. Combining the engineering estimation method and CFD simulation method,the effect on the controllability of the aircraft during the wings folding process were analyzed. Flight test results indicate that the aircraft tend to the dive motion when the wings folded,and the sensitivity of the pitching motion declines gradually with the increase of the trim rudder deflection. Under the condition of same joystick offset,the pitching motion with wings folding state has a faster response speed.

关 键 词：折叠机翼 变体飞机 操纵性 稳定性 

分 类 号：V212.12[航空宇航科学与技术—航空宇航推进理论与工程]