北京航空航天大学学报 ›› 2009, Vol. 35 ›› Issue (1): 74-77.

• 论文 • 上一篇    下一篇

纵列式直升机配平计算及稳定性、操纵性分析

李国知, 曹义华, 杨 倩   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2008-02-20 出版日期:2009-01-31 发布日期:2010-09-16
  • 作者简介:李国知(1984-),男,湖南汉寿县人,硕士生,liguozhibuaa@163.com.

Analysis for determining trim, stability and controllability of tandem helicopter

Li Guozhi, Cao Yihua, Yang Qian,   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2008-02-20 Online:2009-01-31 Published:2010-09-16

摘要: 为了进行纵列式直升机定直平飞状态的配平计算,建立了两种非线性飞行动力学模型(涡流理论模型和动量理论模型).提出了基于线性小扰动理论和五点中心差分算法的稳定性、操纵性导数计算方法;采用状态空间表达式形式的动力学方程,计算了纵列式直升机非耦合运动状态下的稳定根;以动量理论模型为基础,以MATLAB软件为计算平台,进行了纵列式直升机稳定性与操纵性的分析.最终计算结果与参考数据吻合较好,为纵列式直升机飞行品质研究奠定了基础.

Abstract: Two nonlinear tandem helicopter dynamic models (i.e. the vortex theory model and the momentum theory model) were built separately to trim the helicopter at the hover in the forward and backward flight. A computational method for the stability and controllability derivatives was proposed based on the linear perturbation theory and five-point central difference algorithm. The stability roots of the tandem helicopter in the uncoupled mode were computed using the dynamic equations in the state-space form. Based on the momentum theory model, the stability and controllability of the tandem helicopter were analyzed through using the MATLAB software as the computational platform. The agreement between the computational results and the referenced data indicates that the models are feasible and effective, and they can lay the foundation of the research about the tandem helicopter-s flying qualities.

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发