Development of an innovative noise generation system for turboprop aircraft fuselage testing

• Published in: IOP conference series. Materials Science and Engineering Vol. 1226; no. 1; pp. 12053 - 12060
• Main Authors: Dal Borgo, M, Alvarez, M, Blanco, S, Ophem, van, Denayer, H, dell’Aversana, P, Polito, T, Staibano, L, Bianco, R, Peeters, B, Pluymers, B, Desmet, W
• Format: Journal Article
• Language: English
• Published: Bristol IOP Publishing 01.02.2022
• Subjects: Aircraft; Aircraft compartments; Aircraft noise; Airframes; Broadband; Control systems; Cost analysis; Excitation; Feedback control; Flow control; Fuselages; Loudspeakers; Microphones; Noise generation; Noise reduction; Optimization; Output feedback; Regional development; Signal distribution; Test equipment; Turboprop aircraft; Turbulent boundary layer; Waveforms
• ISSN: 1757-8981; 1757-899X
• DOI: 10.1088/1757-899X/1226/1/012053

Abstract This paper presents the development of a cabin noise testing equipment that will be used to evaluate the interior noise of regional aircraft as well as to aid the development of noise reduction techniques. The innovative noise generation system consists of three loudspeaker arrays positioned around the fuselage circumference to synthesize a pressure field that is similar to the pressure field seen by the fuselage during a flight. The acoustic pressure field generated by the loudspeakers is measured by a number of microphones scattered on the fuselage surface. These microphone signals are then fed back to the controller with the purpose of minimising the error between the target pressure field and the measured one by means of an iterative learning approach. The number and location of the microphones used in the control loop are selected through a pre-test optimisation analysis, which aims to reduce the time and cost of the set-up. A small-scale electroacoustic demonstrator has been built to develop the feedback control approach. A frequency domain multi-input multi-output feedback controller is used to replicate the random pressure field generated by the turbulent boundary layer excitation. The multi-harmonics of the propeller induced excitation are then added to the time histories of the broadband noise using a time waveform replication technique. Different arrangements of the driving signal distribution are investigated, and the results are then presented in terms of accuracy of the pressure field reproduction.