Design and Analysis of a Wind Tunnel Test Model System for Rolling Maneuver Load Alleviation of Flying Wings

Design of an aeroelastic model system used in the wind tunnel test of rolling maneuver load alleviation using active controls is discussed in this paper. The system consists of a full-span flying wing aircraft, a connecting mechanism which has a roll degree of freedom with roll angle limiting function, and a real-time control system for data collecting, test situation monitoring and real-time control. The full-s pan flying wing aircraft is a low s peed wind tunnel flutter model. Each wing of it has three control surfaces and its head structure could be removed by other Configuration. Performance of the dynamic characteristics of vibration of the model is analyzed and the flutter velocity is calculated. A system which keeps the aircraft remaining horizontal before starting rolling maneuver is designed by using active control technology.