Modeling and Wind Tunnel Test Validation of a Hybrid Compound High-Speed Helicopter

• Published in: 2023 3rd International Conference on Robotics, Automation and Artificial Intelligence (RAAI) pp. 101 - 106
• Main Authors: Yin, Xinfan, Ma, Hongxu, An, Honglei, Peng, Xianmin, Zhang, Guichuan, Nie, Bowen
• Format: Conference Proceeding
• Language: English
• Published: IEEE 14.12.2023
• Subjects: Aerodynamics; flight dynamics modeling; helicopter; Helicopters; hybrid compound high-speed helicopter; Mathematical models; model validation; Reliability engineering; Rotors; Stability analysis; wind tunnel test; Wind tunnels
• DOI: 10.1109/RAAI59955.2023.10601283

Taking a hybrid compound high-speed helicopter with strong realizability, excellent vertical take-off and landing performance and high cruise velocity as the research object, nonlinear flight dynamics model is conducted based on Newton-Euler method under the premise of basic assumptions. Aiming at the complex unsteady rotor aerodynamics modeling, the blade element theory is used to calculate the aerodynamic force and moment of the rotor, the Pitt-Peters unsteady dynamic inflow model is used to calculate the rotor induced velocity, and the equivalent flapping torsion spring method is used to establish the flapping motion model. The wind tunnel test results indicate that the trim results of the hybrid compound high-speed helicopter flight dynamics mathematical model established in this paper have a good consistency with the wind tunnel test results and in accord with the flight state and control law of the hybrid compound high-speed helicopter, which objectively proves that the nonlinear flight dynamics model has a high level of confidence.