摘要
结合较高精度和可靠性的旋翼刚柔耦合动力学模型和旋翼自由尾迹空气动力学模型,建立包含主动控制后缘襟翼(Active control trailing edge flap,ACF)的旋翼桨涡干扰气弹耦合分析模型,开展基于ACF主动控制技术的旋翼桨毂振动载荷控制。分析旋翼前进比、ACF控制频率和初始相位对桨毂振动载荷控制效果的影响,得到桨涡干扰情况下ACF对旋翼桨毂载荷的振动控制机理,仿真分析表明,在前进比为0.15时,3倍频的ACF最佳控制相位为300°,4倍频的ACF最佳控制相位为270°,前进比为0.12时,4倍频的ACF最佳控制相位变为190°。研究得到ACF控制规律如下:ACF在桨盘50°~80°方位为最小正偏角时可以有效降低桨毂振动载荷;而当ACF在桨盘50°~80°方位为最大正偏角时不利于桨毂振动载荷的控制。基于此控制规律,在ACF旋翼风洞试验台上开展ACF开环控制的验证试验。结果表明,试验数据与仿真计算规律相吻合,提出的ACF控制策略对前进比为0.12和0.15的来流工况下的旋翼桨毂振动载荷均可实现有效降低。
Combining the rigid-flexible coupling dynamics model of the rotor with high precision and reliability and the aerodynamic model of rotor free-wake,an aeroelastic coupling model with blade vortex interaction including active control trailing edge flap(ACF)is established and the dynamic load control of the rotor hub based on ACF active control technology is carried out.The influence of advance ratio of rotor,control frequency of ACF and initial phase on control effect of vibration load of rotor hub were analyzed.The vibration control mechanism of ACF on rotor hub load under the condition of blade vortex interaction is obtained.The simulation analysis shows that when advance ratio is 0.15,the optimal control phase of ACF under 3/rev control is 300°and that for 4/rev control is 270°.When the advance ratio is 0.12,the optimal control phase of ACF with 4/rev control becomes 190°.It is found that the ACF can effectively reduce the vibration load of the hub by controlling the initial phase so that the ACF has the minimum positive deflection at the blade vortex interaction region,while the control of the vibration load of the hub is not beneficial when the ACF has the maximum positive deflection at the blade vortex interaction region.The validation test of ACF open-loop control was carried out on the ACF rotor wind tunnel test bench.The results show that the test data conform to the control law presented,and the proposed control strategy can effectively reduce the vibration loads of rotor hub under different inflow conditions.
作者
周子宣
田嘉劲
唐敏
王畅
黄修长
华宏星
ZHOU Zixuan;TIAN Jiajin;TANG Min;WANG Chang;HUANG Xiuchang;HUA Hongxing(State Key Laboratory of Mechanical System and Vibration,Shanghai Jiao Tong University,Shanghai 200240;Shanghai Aircraft Design&Research Institute,Shanghai 200240;China Aerodynamic Research and Development Center,Mianyang 621050)
出处
《机械工程学报》
EI
CAS
CSCD
北大核心
2023年第14期254-263,共10页
Journal of Mechanical Engineering
基金
国家自然科学基金创新群体资助项目(12121002)。
关键词
主动后缘襟翼
桨涡干扰
桨毂振动
主动控制
active controlled flap
blade vortex interaction
hub vibration
active control
