直升机自动过渡悬停飞行控制系统设计  

Design of Automatic Transition and Hovering Flight Control System for Helicopter

作　　者：杨一栋[1] 黄屹[1] 李林华[2] 

机构地区：[1]南京航空航天大学自动化学院,南京210016 [2]中国航空工业总公司第602研究所,景德镇333001

出　　处：《南京航空航天大学学报》2004年第2期200-204,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：航空科学基金 (0 1 E5 2 0 8)资助项目

摘　　要：为实现直升机自动过渡悬停功能 ,在具有优良操纵特性的直升机显模型跟踪控制系统 (MFCS)基础上 ,开发了自动过渡悬停控制系统。根据过渡悬停机动模态的基本要求 ,设计了高度控制回路 ,以实现高度通道按抛物线下降 ,接着进行线性下降并最终过渡到指数拉平。设计了纵向速度控制回路 ,使速度先按指定的减加速度线性减速 ,再按指数规律减速至悬停 ,且两通道之间协调控制 ,保证当直升机高度接近悬停高度时 ,纵向速度同步地趋近于零。文中给出了系统结构配置及参数设计方法。仿真表明 ,本文直升机自动过渡悬停系统具有优良的物理特性。To realize the automatic transition and hovering capability for helicopter,automatic transition and hovering flight control system is developed based on helicopter model following control system (MFCS). The system has an excellent operation characteristic. According to the basic requirements of the mode, height control loop and portrait velocity control loop are designed to accomplish the specific flight maneuver. During the automatic transition and hovering process, the height of helicopter descends in parabola track firstly, after that, the descendent velocity becomes a constant value till the helicopter entering the exponential flare path. The portrait velocity decreases in constant deceleration firstly and in exponentially variational deceleration finally. The two loops cooperate together to guarantee that the velocity decreases to zero synchronously with the height descending to the expected height. The configurations of two loops and the system parameter designing method are expounded and a simulation is processed. The simulation indicates that the automatic transition and hovering flight control system for helicopter has an excellent physical feasibility.

关 键 词：直升机 自动过渡悬停 飞行控制系统 设计 显模型跟踪控制系统 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] V275.1