摘要
为了研究直升机在风切变气流场中的响应特性,基于相关文献,建立了风切变工程化模型。根据旋翼的非均匀入流模型,建立了直升机非线性动力学模型,并利用四阶龙格—库塔法,对某型直升机在风切变场中的飞行特性进行了数值仿真。研究结果表明:样机进入风切变场后,飞行姿态立即出现俯仰震荡、左右摇摆的现象,10 s内,侧倾角的峰值差最大达到了73.14°,直升机下坠的高度为53.19 m,偏航距离为93.79 m。
For the purpose of studing the response of helicopter in wind shear field, the wind shear model was established based on reference. The complete helicopter flight dynamic model was established when considering the non-uniform inflow of main rotor, and Runge-Kutta technique was used to solve the equations. It was found that from the results, the wind shear made the attitude angle shake, which deteriorated the stability of helicopter. Especially peak values of the roll angle difference reached to 73.14 degrees. The windshear had greater effect on the helicopter＇s track, The results showed that falling distance could be up to 53.19 m and yaw distance could be up to 93.79 m in 10 seconds.
出处
《海军航空工程学院学报》
2013年第2期146-150,共5页
Journal of Naval Aeronautical and Astronautical University
关键词
直升机
风切变
动态响应
飞行动力学
helicopter
wind shear
dynamic response
flight dynamics
