Many vibrating systems when experimentally tested show weak non-linear
ity. In these cases linear response features such as natural frequenci
es and damping ratios though clearly identifiable, nevertheless show a
mplitude dependency. This paper describes an approach where the underl
ying non-linear differential equation governing the system may be iden
tified. As input the equivalent linear response parameters measured ov
er a range of amplitudes are used. A commercial aircraft trim panel mo
unting is considered as an example to demonstrate the technique. (C) 1
995 Academic Press Limited