摘要
描述了旋翼飞行器飞行力学模型的系统辨识建模算法,从旋翼飞行器飞行动力学建模的共性问题入手,首先采用机理建模的方法分析了旋翼飞行器主要气动部件所受气动力。考虑旋翼挥舞运动对旋翼飞行器飞行动力学特性的影响,建立了旋翼飞行器的飞行力学系统辨识参数化模型集。其次以子空间方法辨识初始飞行动力学模型,采用加权频域预报误差法获得最优模型的两步辨识方法解决旋翼飞行器这一非线性不稳定,多输入-多输出系统辨识问题,且所辨识模型与机理模型具有相同的结构。最后对样例直升机的悬停飞行状态模型辨识进行了数值与试飞试验验证,表明了方法的有效性。
Based on common characteristics of rotorcraft flight mechanics modeling,theories and algorithm of model identification are studied.Firstly,by using mechanism modeling method and considering blades flapping,the parameter identification model group is established.Secondly,in order to solve multi input and output system identification problems,a two step identification method is proposed.It identifies the initial model by subspace identification method and then the optimized model by frequency prediction error method.Finally,with this two-step identification method,the simulation and flight tests are conducted to identify the example helicopter flight mechanics model in the hover state.The result shows that the method is effective and accurate.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2011年第3期387-392,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(60705034)资助项目
关键词
飞行动力学
系统辨识
旋翼飞行器
子空间法
预报误差法
flight dynamics
system identification
rotorcraft
subspace method
prediction error method
