Fig.1

Structural model of wing with control surface

Fig.2

First four modes of wing model with control surface

Table 1

Comparison of mode frequencies between modal test of wing with control surface and simulation of updated dynamic finite element model

Fig.3

Configuration scheme for aerodynamic force loading points/response measurement points

Table 2

MACmatrix of first four mode shapes for reduced-order model

Fig.4

Comparison for flutter characteristics of wing with control surface before and after reduction

Table 3

Flutter characteristics of wing with control surface before and after reduction

Fig.5

Input signal of exciter-structure system

Fig.6

Exciter output force of exciter-structure system

Fig.7

Comparison of frequency response functions between identified model and experimental test

Fig.8

Model relative error and frequency response of W3(1,1)

Fig.9

Tracking performance of robust controller

Fig.10

Ground flutter simulation test platform for wing with control surface

Fig.11

Comparison of excitation force and target aerodynamic force of Channel 4 at V=81 m/s

Fig.12

Displacement response spectrum of Channel 4 at V=81 m/s

Fig.13

Comparison of excitation force and target aerodynamic force of Channel 4 at V=81.5 m/s

Fig.14

Displacement response spectrum of Channel 4 at V=81.5 m/s

Fig.15

Comparison of excitation force and target aerodynamic force of Channel 4 at V=82 m/s

Fig.16

Displacement response spectrum of Channel 4 at V=82 m/s

Table 4

Comparison of ground flutter simulation test result with calculation result

Fig.17

Schematic of freeplay nonlinearity for wing with control surface

Fig.18

Comparison of excitation force and target aerodynamic force of Channel 4 at V¯ =0.6

Fig.19

Displacement response spectrum of Channel 4 at V¯ =0.6

Fig.20

Variation of LCO amplitude with non-dimensional velocity

Fig.21

Variation of non-dimensional LCO frequency with non-dimensional velocity