摘要
根据Hamilton原理,采用中等变形梁理论,将桨叶离散为15自由度梁单元,用准定常气动模型建立旋翼/刚性机身耦合的有限元非线性方程,用时间有限元法进行气弹耦合配平计算,得到桨叶和机身运动的周期解.在此基础上,引入Peters动态入流模型分析耦合系统的稳定性.并研制相应的计算程序,可用于桨叶响应、桨叶和桨毂载荷、旋翼操纵等方面的分析计算.算例分析结果与相关文献吻合较好,且同时满足桨叶响应和配平方程的收敛性要求.
Based on the principle of Hamilton and the moderate deflection beam theory, discretizing the blade into a number of beam elements which had 15 degrees of freedom, using quasi-steady aero model, the nonlinear coupled rotor/fuselage equation was founded. The periodic solution of blades and fuselage were obtained through aeroelastic coupled trim using temporal finite element method. Peters＇ dynamic inflow model was adopted for vehicle stability. A calculation program was built up, which offered the blade responses, hub loads and the rotor pitch controls. The correlation between analytical results and related literatures is good. The converged solution simultaneously satisfies the blade and the vehicle equilibrium equations.
出处
《应用数学和力学》
CSCD
北大核心
2010年第2期218-226,共9页
Applied Mathematics and Mechanics
基金
国家自然科学基金资助项目(10872089)
关键词
非线性
气弹响应
旋翼/机身耦合
时间有限元法
稳定性
nonlinear
aeroelasticity
rotor/fuselage coupling
temporal finite element method
stability
