总距突增时共轴式直升机瞬态操纵响应分析

聂资; 陈铭; 徐冠峰

总距突增时共轴式直升机瞬态操纵响应分析

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2.
中国人民解放军陆军航空兵学院, 北京 101123

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出版历程
- 收稿日期: 2011-08-05
- 修回日期: 2011-12-26
- 刊出日期: 2012-03-28

Dynamic response analysis of a small-scale coaxial helicopter to a rapid collective pitch increase

1.
School of Aeronautics Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
Army Aviation Institute, The Chinese People’s Liberation Army, Beijing 101123, China

摘要

摘要: 从共轴双旋翼直升机的工程实际出发,建立了共轴式直升机上下旋翼非定常气动特性的计算模型.引入Leishman-Beddoes指数函数的半经验公式,建立了二维翼型非定常气动模型;分别从固定尾迹和自由尾迹,引入干扰因子到动态入流三种方法出发,建立了反映共轴双旋翼直升机上下旋翼气动干扰的诱导速度模型;从跷跷板式旋翼的挥舞动力学方程出发,利用4阶Runge-Kutta算法求解桨叶刚性挥舞角的数值解.通过计算分析,得到了悬停和前飞状态,总距突增时上下旋翼升力的动态响应特性,以及总距突增时上下旋翼桨叶铰链力矩的响应特性.
- 共轴式直升机 /
- 旋翼非定常 /
- 诱导入流 /
- 总距突增 /
- 动态响应
Abstract: Based on the engineering reality,a calculation model of the rotor unsteady aerodynamics of the small-scale coaxial helicopter had been set up.An airfoil unsteady aerodynamic model was established by introducing a set of Leishman-Beddoes semi-empirical indicial response formula.The induced velocity of the aerodynamic interaction between upper and lower rotors of a coaxial helicopter was set up based on the rigid wake model,free wake model and the dynamic inflow model with interference factors.Considering the teetering rotor’s particular flapping dynamic formula,the Runge-Kutta method was used to obtain the numerical solution of the rigid blade flapping angle.According to the calculation and analysis,the thrust response to a rapid collective pitch increase in both the hovering and forward flight states were obtained,and the blade’s hinge moment of the upper and lower rotors were compared.
- coaxial helicopter /
- rotor unsteady /
- induced inflow /
- rapid collective pitch increase /
- dynamic response

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参考文献(12)

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