摘要
对变体飞机机翼变形时的飞行动力学响应进行仿真,分析机翼变形诱导出附加力及力矩的影响,为变体飞机飞行控制提供参考依据.基于牛顿欧拉方程,推导出适用于变体飞机的扩展运动方程,方程中增加了4项由于机翼变形而产生的附加力及附加力矩.基于涡格法建立任意机翼构型下气动力求解方法.将变体机翼飞机的动力学建模与仿真分析方法应用于M型机翼变体飞机,对机翼对称及非对称变形下的动力学响应进行分析.结果表明,附加力及附加力矩对变体飞机飞行影响明显.
The dynamic response of morphing simulated, and the additional forces and moments aircraft in the wing morphing process was induced by wing morphing were analyzed. The result would be taken as reference for flight control of morphing aircraft. Based on Newton-Euler equations, the extended motion equations suitable for morphing aircraft were developed, in which 4 additional forces and moments were added due to the wing morphing. Vortex lattice method was used to find out the aerodynamic properties of variable wing configurations. The modeling and simulation methodology was applied to M-wing aircraft, and the dynamic response of the aircraft was analyzed with the wing changes symmetrically or asymmetrically. The result shows that the aircraft was affected significantly by the additional forces and moments.
出处
《北京理工大学学报》
EI
CAS
CSCD
北大核心
2013年第2期127-132,共6页
Transactions of Beijing Institute of Technology
