摘要
主要阐述直升机贴地飞行时的驾驶员诱发振荡问题，导出了贴地突防和迅速停止动作、地形跟踪时的“海豚”运动和贴地飞行时滑雪运动条件下诱发振荡时操纵位移和稳定裕度的计算公式，计算了Ｚ─８直升机的纵向试验结果，并进行了误差分析。计算结果表明，所研究的方法是可行的，可推广应用于各种直升机的闭环分析和计算。
This paper describes a method for determine pilot induced oscillation undercondition of helicopter NOE, the calculation formula for control displacement under inducedoscillation and stability margin have been derived with breakthrough a defence line and quickstop under condition of NOE, dolphin movement under the condition of terrian flight andslalom movement under the condition of NOE, longitudinal test results have been calculatedbv the method,and test error have been analysed.Calculated results show that the methodis feasible,suitable to any helicopter closed-loop analyses and calculations.
出处
《飞行力学》
CSCD
北大核心
1995年第2期45-50,共6页
Flight Dynamics
关键词
直升机
振荡
驾驶员诱发振荡
稳定性裕度
Helicopter pilot induced oscillation Stability margin Nonlinear closedloop stability
