This paper focuses on the localization of impacts applied on a composite aircraft by using low sampling frequency accelerometers. A new vibration-based approach using a modal model of the aircraft on ground is described to localize the impact on the cylindrical fuselage. Axial localization is achieved by estimating the contributions of specific vibration modes to the response. Angular localization is achieved by estimating the impact force direction. An impact test campaign is performed on an Airbus A350-900 equipped with only six accelerometers. Fifty percent of the applied impacts are localized within 2 m and more than 90% within 3 m.

In long range aircraft, one reason of discomfort of the passengers are the vibrations and the noise induced by the rotation of the engine. This induces high-level single-frequency excitations (both for noise and vibration). The frequency (located between 25 and 55 Hz) and the amplitude of these excitations vary depending on flight parameters. This study investigates the influence of the frequency and the level of vibration and noise stimuli to discomfort. The aim is to build a global discomfort model. Subjective experiments were carried out in the laboratory, on a test bench allowing to control vibration and noise stimuli. Volunteers separately assessed the vibration, noise and global discomfort. Foot, seat, backrest and armrests accelerations were measured for each participant and each stimulus. As expected, noise or vibration discomfort depends on the excitation level; but no influence of the frequency could be detected. Finally, it appears that specific vibration discomfort strongly influences global discomfort.

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