Abstract
In order to perform damage detection, life prediction and redesign of
critical aeroplane components - as for instance the slat track, which
extends the surface of the wing at take-off and landing - it is
essential to obtain an accurate modal model. In particular, information
from a limited number of sensors has to be processed to track the
change of the modes during fatigue loading.
In this article, an experimental procedure to estimate modal parameters
with a high accuracy is proposed. Efforts where made to make the
measurement time as low as possible. The method consist of three steps
: an automatic laser scanning procedure, an optimal excitation design
and an optimal sensor location step. Validation results on a slat track
are presented.
critical aeroplane components - as for instance the slat track, which
extends the surface of the wing at take-off and landing - it is
essential to obtain an accurate modal model. In particular, information
from a limited number of sensors has to be processed to track the
change of the modes during fatigue loading.
In this article, an experimental procedure to estimate modal parameters
with a high accuracy is proposed. Efforts where made to make the
measurement time as low as possible. The method consist of three steps
: an automatic laser scanning procedure, an optimal excitation design
and an optimal sensor location step. Validation results on a slat track
are presented.
| Original language | English |
|---|---|
| Title of host publication | Proceedings of the 20th International Modal Analysis Conference, p. 1138-1143, Los Angeles (USA), February 2002 |
| Publisher | Proceedings of the 20th International Modal Analysis Conference, p. 1138-1143, Los Angeles (USA), February 2002 |
| Publication status | Published - 2002 |
| Event | Unknown - Duration: 1 Jan 2002 → … |
Conference
| Conference | Unknown |
|---|---|
| Period | 1/01/02 → … |
Bibliographical note
Proceedings of the 20th International Modal Analysis Conference, p. 1138-1143, LosAngeles (USA), February 2002