摘要
建立了带后缘小翼智能旋翼气动弹性载荷计算模型及减振优化分析方法。模型考虑刚体后缘小翼的气动力与惯性力对弹性桨叶系统的影响,使用粘性涡粒子法结合翼型查表法计算旋翼气动载荷,采用力积分法计算桨叶与桨毂载荷,构造了包含桨叶根部扭转及桨毂振动载荷为目标函数的优化问题,基于最速下降-黄金分割组合优化算法寻找最佳小翼偏转规律。研究发现,建立的后缘小翼载荷控制方法有效,可降低振动目标函数70%。桨叶的弹性扭转使后缘小翼能有效实施减振,但弹性扭转对小翼气动力矩的放大作用使减振时通常伴随着桨叶扭转载荷增大的现象。
An aeroelastic load computation model and the optimization method of vibration control for a smart rotor wing with trailing edge flags were developed. The influences of aerodynamic forces and inertial forces of rigid body trailing edge flaps on its elastic blades system were considered. The viscous vortex particle method with the airfoil look-up table was used to compute the aerodynamic load of the rotor wing. The vibratory blade and hub loads were predicted with the force integration method. An optimal algorithm combining the steepest decent method and the golden section algorithm was derived for the defined objective function including the blade torsion and hub vibration loads. It was demonstrated that the proposed model can effectively control the vibratory loads, and the objective function can be reduced by about 7 0 % ; the torsion of elastic blades ensures the trailing edge flaps can effectively reduce vibration, while it amplifies the aerodynamic pitch moment of the trailing edge flaps, the latter brings additional blade torsional moment.
出处
《振动与冲击》
EI
CSCD
北大核心
2017年第3期138-144,共7页
Journal of Vibration and Shock
基金
国家自然科学基金(11272148)
江苏高校优势学科建设工程
旋翼动力学国防科技重点实验室基金(9140C400401140C40183)
关键词
直升机
旋翼
振动
后缘小翼
优化方法
helicopter
rotor wing
vibration
trailing edge flap
optimization method
