直升机航向模态切换方法设计  

Design for Switching Method of Helicopter Yaw Mode

作　　者：明星 史青海[1] MING Xing;SHI Qing-hai(China Helicopter Research and Development Institute,Jingdezhen Jiangxi 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《机械研究与应用》2018年第3期111-112,115,共3页Mechanical Research & Application

摘　　要：通过对直升机协调转弯和航向稳定功能进行数据分析,在模态切换过程中会出现控制律输出变化大,航向姿态变化大的现象。针对直升机协调转弯存在的具体问题,设计了退出协调转弯进入到航向稳定模态过程的瞬态平滑处理方法,以克服退出转弯时的航向抖动问题。经试飞验证,该方案有效可行,起到了从协调转弯模态进入航向稳定模态的平滑过渡,抑制了航向瞬态变化大的现象。Through the data analysis of helicopter coordinated turning and heading stability functions,there will be great changes of control law output and heading attitude in the mode switching process.Aiming at the specific problem of coordinated turn for helicopters,a transient smoothing method is proposed to adjust the process of the coordinated turn to heading stabilization,so as to overcome the problem of heading jitter when exiting the turn.It is proved by test flight that the scheme is effective and feasible.A smooth transition from the coordinated turning mode to the heading stability mode is achieved,which suppresses the phenomenon that the course varies instantaneously.

关 键 词：自动驾驶仪 协调转弯 航向抖动 过渡处理 

分 类 号：V249.12[航空宇航科学与技术—飞行器设计]