Design of a control system for a 1.5 m diameter coaxial rigid rotor model

Abstract

As a key equipment for rotor wind tunnel testing, the design specifications and control accuracy of the rotor test bench directly determine the testing accuracy and effectiveness of the rotor wind tunnel testing. Targeted design 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 control accuracy at rated speed is up to 0.03%, the pitch accuracy of the upper rotor is up to ±0.2°, and the pitch accuracy of the lower rotor is up to ±0.1°, meeting the control accuracy requirements of coaxial rigid rotor wind tunnel tests for the system.

Keywords

• coaxial rigid rotor
• speed control system
• operation control system
• labwindows/cvi
• wind tunnel test