摘要
基于旋翼综合气弹分析程序,求解出直升机旋翼桨叶在飞行过程中的稳态响应。以此作为鸟体撞击桨叶的初始状态,采用非线性流-固耦合算法,建立了直升机旋翼桨叶鸟撞动力学方程,利用直接数值积分方法求解桨叶的动态响应。并讨论了鸟体速度、质量、撞击位置、桨叶根部约束和离心力等参数对桨叶动态响应的影响,从而为直升机桨叶抗鸟撞设计提供一些理论依据。
The steady-state response of a helicopter rotor in flight was solved by using a comprehensive aeroelastic analysis program. The result is then used as an initial state of a bird impact on the blade. The dynamic equation of helicopter rotor blade under bird impact was established by adopting non-linear fluid-solid coupling algorithm. Then the dynamic response of blades was solved by using direct numerical integration method. To provide some theoretical basis for the design of anti-bird-impact helicopter blade, the system parameters such as bird speed, bird quality, impact location, blade root constraint and rotating speed were discussed.
出处
《振动与冲击》
EI
CSCD
北大核心
2013年第10期62-68,共7页
Journal of Vibration and Shock
