航空工程进展2025，Vol.16Issue(3)：198-205,8.DOI:10.16615/j.cnki.1674-8190.2025.03.21
1.5 m直径共轴刚性旋翼模型控制系统设计
Design of a control system for a 1.5 m diameter coaxial rigid rotor model
刘实 1邵天双 1刘向楠1
作者信息
- 1. 中国航空工业空气动力研究院 低速高雷诺数航空科技重点实验室,哈尔滨 150001
- 折叠
摘要
Abstract
As a key equipment for rotor wind tunnel testing,the design specifications and control accuracy of the ro-tor test bench directly determine the testing accuracy and effectiveness of the rotor wind tunnel testing.Targeted de-sign of the coaxial rigid rotor test bench structure and control system is the key to exploring the influence of specific parameters on the aerodynamic characteristics of high-speed helicopters.A 1.5 m diameter coaxial rigid rotor test bench is developed,and a 1.5 m coaxial rotor model control system based on vector closed-loop variable frequency speed regulation and electronic control servo technology is designed.The system hardware integration and software function development based on LabWindows/CVI environment are completed.The system is tested and verified in the FL-52 open-loop wind tunnel for hovering and forward flight conditions.The results show that the system has good dynamic response speed and control accuracy,and can maintain good control stability at high speed.The con-trol accuracy at rated speed is up to 0.03%,the pitch accuracy of the upper rotor is up to±0.2°,and the pitch accu-racy of the lower rotor is up to±0.1°,meeting the control accuracy requirements of coaxial rigid rotor wind tunnel tests for the system.关键词
共轴刚性旋翼/转速控制系统/操纵控制系统/LabWindows/CVI/风洞试验Key words
coaxial rigid rotor/speed control system/operation control system/LabWindows/CVI/wind tunnel test分类
航空航天引用本文复制引用
刘实,邵天双,刘向楠..1.5 m直径共轴刚性旋翼模型控制系统设计[J].航空工程进展,2025,16(3):198-205,8.
