机电工程技术2025，Vol.54Issue(21)：25-28,95,5.DOI:10.3969/j.issn.1009-9492.2025.21.005
基于FlightLab的共轴双旋翼直升机建模和仿真
Modeling and Simulation of Coaxial Dual-rotor Helicopters Based on FlightLab
岳杰顺 1邢立业1
作者信息
- 1. 北京中航智科技有限公司,北京 100176
- 折叠
摘要
Abstract
Coaxial rigid dual-rotor helicopters have the advantages of small size,compact structure,excellent performance,and high maximum speed.The design of control system is a challenging aspect in the design of coaxial dual-rotor helicopters.A flight dynamics model and a control decoupling model are established for a coaxial dual-rotor helicopter based on the helicopter simulation software FlightLab,and the control trimming for forward flight conditions is calculated.Comparison with flight test data shows that the calculated control inputs and helicopter attitude angles have relatively small errors across the entire flight speed range,proving the accuracy of the dynamic numerical methods and the established model.Moreover,compared to other common calculation methods,this model is characterized by its simplicity and ease of operation.Further calculations are conducted for the control trimming results of the helicopter under different altitude and weight conditions.Analysis shows that the collective pitch,longitudinal,and lateral control inputs increase with altitude and weight.It particularly noticeable affects the collective pitch and longitudinal control.The research result provides a basis for the design of control mechanisms and control systems.关键词
FlightLab/共轴双旋翼直升机/飞行力学/操纵配平/姿态角/控制系统Key words
FlightLab/coaxial dual-rotor helicopter/flight dynamics/trimming/attitude angle/control system引用本文复制引用
岳杰顺,邢立业..基于FlightLab的共轴双旋翼直升机建模和仿真[J].机电工程技术,2025,54(21):25-28,95,5.
