摘要
利用MATLAB/SIMULINK平台搭建了直升机仿真实验系统,并以UH-60直升机为对象实现了考虑非理想噪声干扰的仿真飞行实验。建立了非理想噪声数学模型并基于增广最小二乘法设计了一套同时考虑模型参数和噪声参数的综合辨识算法,在此基础上,利用仿真实验数据实现了UH-60直升机纵向飞行动力学模型的辨识与验证。最后,通过与普通最小二乘法的对比验证了本文方法的优越性。
A simulation system for helicopters is established in MATLAB/SIMULINK platform, and the flight simulation test of a UH-60 helicopter considering the non-ideal noise is implemented. A mathe- matical model of the non-ideal noise is built, and a comprehensive identification method is designed based on the recursive extended least squares which can identify the model parameters and noise parame- ters simultaneously. The identification and verification of the longitudinal flight dynamics model of a UH-60 helicopter are realized by using the simulation test data. Finally, the proposed method is com- pared with the least square method. Results prove the superiority of the method.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2016年第2期224-229,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(61503183)资助项目
航空科学基金(2015ZA52002)资助项目
江苏省高校优势学科建设工程资助项目
关键词
直升机
飞行动力学
系统辨识
非理想噪声
helicopter
flight dynamics
system identification
non-ideal noise
