摘要
针对轮式起落架直升机,提供了一种“舰面共振”动力稳定性分析方法。首先,针对直升机在舰面上随舰船一起摇晃时左右起落架受载不对称的状况,近似采用受对称载荷产生对称变形、受非对称载荷产生非对称变形的方法计算了直升机的平衡状态;其次,根据轮式起落架轮胎和缓冲支柱刚度和阻尼共同作用的特点,结合轮式起落架的几何关系,采用复刚度的方法得出起落架作用于机体的刚度与阻尼;最后,用桨叶振动模态法对轮式起落架的直升机进行了不同旋翼升力卸载以及鱼叉系留与否的“舰面共振”动力稳定性计算分析,并通过算例得到验证。
An analytical method of ship resonance dynamic stability countering the helicopter with wheel landing gears is provided. Firstly, according to the characteristics of landing gears acted unsymmetrically with helicopter reeling on ship, the helicopter trim is calculated approximately using the method that landing gears is deformed symmetrically by symmetrical forces and unsymetrically by unsymmetrical forces. Secondly, the stiffness and damp of landing gears are gotten by complex stiffness with the geometry relationship of wheel landing gears. Finally, the analysis of ship resonance dynamic stability of helicopter with wheel landing gears is preformed by using blade vibration modal method to different rotor lift forces and harpoon deck-lock or no deck-lock. The analytical method is verified by examples.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2007年第4期886-890,共5页
Acta Aeronautica et Astronautica Sinica
关键词
直升机
舰面共振
轮式起落架
动力稳定性
桨叶振动模态法
鱼叉系留
helicopter
ship resonance
wheel landing gear
dynamic stability
blade vibration modal method
harpoon deck-lock
