Fig.1

Calculation of maneuver flight loads for modern aircraft［10］

Fig.2

Variation of aerodynamic load distribution［16］

Fig.3

Calculating process of flight loads for military aircraft［18］

Fig.4

Modelling process for Maneuver Load Control （MLC） system［16］

Fig.5

Deformation of aerodynamic grids［33］

Fig.6

Aerodynamic model of unsteady vortex-lattice method［35］

Fig.7

Surface pressure distribution obtained by high-order panel method［36］

Fig.8

Process of elastic aerodynamic force calculation based on tight coupling method［40］

Fig.9

Model of beam-frame structure［50］

Fig.10

Modal analysis of equivalent plate method［51］

Fig.11

Central wing box FEM of high aspect ratio wing［52］

Table 1

Radial basis function［64］

Fig.12

Transmission of aerodynamic force to structural grids［68］

Fig.13

Comparison of neighborhood correction method and RPIM method［69］

Fig.14

Analysis method for maneuver process

Fig.15

Load envelope［18］

Fig.16

Procedure of wind tunnel test［19］

Fig.17

Aero-servo-elastic system for maneuver load alleviation［16］

Fig.18

PID control diagram［16］

Fig.19

Surrogate model for flight load analysis process

Fig.20

Random forest model［135］

Fig.21

Comparison of real values and predicted values ［135］

Fig.22

Structure of whole vehicle and sensor arrangement［111］

Fig.23

Test measurement and control system［111］

Fig.24

Comparison of loads for baseline control and control law 1［111］

Fig.25

Comparison of loads for baseline control and control law 2［111］

Fig.26

Illustration of FFast right wing［149］

Fig.27

Illustration of aeroelastic model discretization［149］

Fig.28

Shear force， bending moments and torque diagrams of FFast wing during 2.5g maneuver ［149］

Fig.29

Normalized virtual shape functions with markers indicating Smart X-Alpha servo locations［117］

Fig.30

Seamless active morphing wing Smart X-Alpha with TRIC morphing mechanism［117］

Fig.31

Performance of INDI-QP-V in challenging maneuver load alleviation task［117］

Fig.32

Structural FEM of simulation object［113］

Fig.33

Trailing-edge model of continuous variable camber［113］

Fig.34

Architecture of roll maneuver control system for elastic aircraft［113］

Fig.35

Curves of bending moment at wing root against time［113］

Fig.36

Ground modal test of wind tunnel test model［113］

Fig.37

Result comparison of wind tunnel test and simulation ［113］