摘要
本文是在对某机尾旋特性研究的基础上,探讨引入副翼-方向舵交联系统和稳定轴偏航阻尼器对该机尾旋进入特性的影响,看其抗偏离/尾旋效果.研究方法仍采用微分方程的分支突变理论,结合时域动态响应,计算装有这类控制系统后的飞机平衡面等.
In the paper, the effects of Aileron-Rudder-Interconnect (ARI) and stability-axis yaw damper on spin behavior are explored by the Bifurcation Analysis and Catastrophe Theory Method (BACTM) combining with the check of time history for an aircraft. The results show that the systems are effective in preventing the departure/spin of the aircraft.
出处
《飞行力学》
CSCD
北大核心
1991年第2期1-10,共10页
Flight Dynamics
关键词
副翼
方向舵
变联系统
阻尼器
尾旋
aileron-rudder-interconnect
stability-axis yaw damper
departure
spin.
