Sandwich structures with lattice cores are novel, lightweight composite structures and are widely used in the aerospace industry. Besides, the aeroelastic behavior of sandwich panels in a supersonic flow regime still needs to be thoroughly studied. This work investigates the supersonic flutter of a sandwich panel whose core is topology-optimized. A finite element model of a sandwich panel based on the layerwise theory, coupled with the first-order piston theory, is presented. The sandwich panel core is assessed using a topology optimization approach with flutter loading constraints. The subsequent analytical homogenization scheme is developed to provide the equivalent mechanical properties of the topology-optimized panel. The modeling approach is fully validated, and the results demonstrate that the sandwich panel is capable of enlarging the flutter-free operational flight range when compared with other conventional panel designs. A parametric analysis of the topology-optimized sandwich panel regarding the critical flutter conditions is performed.
NjugunaJ. Flutter prediction, suppression and control in aircraft composite wings as a design prerequisite: a survey. Struct Control Health Monit2007; 14: 715–758.
2.
DowellEH. Aeroelasticity of plates and shells. Springer Science and Business Media, 1974, vol 1.
3.
FungYC. An introduction to the theory of aeroelasticity. Courier Dover Publications, 2008.
4.
BisplinghoffRLAshleyH. Principles of aeroelasticity. Boca Raton, FL: Courier Corporation, 2013.
5.
WeiZYamLChengL. Detection of internal delamination in multi-layer composites using wavelet packets combined with modal parameter analysis. Compos Struct2004; 64: 377–387.
6.
PidapartiRChangC. Finite element supersonic flutter analysis of skewed and cracked composite panels. Comput Struct1998; 69: 265–270.
7.
StrganacTWKimYI. Aeroelastic behavior of composite plates subject to damage growth. J Aircraft1996; 33: 68–73.
8.
CastanieBBouvetCGinotM. Review of composite sandwich structure in aeronautic applications. Composites Part C: Open Access2020; 1: 100004.
9.
SongZGLiFM. Aerothermoelastic analysis of lattice sandwich composite panels in supersonic airflow. Meccanica2016; 51: 877–891.
10.
SongZ-GLiF-M. Flutter and buckling characteristics and active control of sandwich panels with triangular lattice core in supersonic airflow. Compos B Eng2017; 108: 334–344.
11.
ChaiYYSongZGLiFM. Investigations on the influences of elastic foundations on the aerothermoelastic flutter and thermal buckling properties of lattice sandwich panels in supersonic airflow. Acta Astronaut2017; 140: 176–189.
12.
ZhuangWZYangCWuZ-G. Aeroelastic analysis of foam-filled composite corrugated sandwich plates using a higher-order layerwise model. Compos Struct2021; 257: 112996.
13.
ZhangJYanZXiaL. Vibration and flutter of a honeycomb sandwich plate with zero Poisson’s ratio. Mathematics2021; 9: 2528.
14.
MucAFlisJ. Closed form solutions--Analysis and optimal design of supersonic composite laminated flat plates considering mechanical and thermal effects. Compos Struct2019; 230: 111491.
15.
SongZ-GLiF-MCarreraE, et al.A new method of smart and optimal flutter control for composite laminated panels in supersonic airflow under thermal effects. J Sound Vib2018; 414: 218–232.
16.
GuoS. Aeroelastic optimization of an aerobatic aircraft wing structure. Aero Sci Technol2007; 11: 396–404.
17.
LiJNaritaY. Multi-objective design for aeroelastic flutter of laminated shallow shells under variable flow angles. Compos Struct2014; 111: 530–539.
18.
De LeonDDe SouzaCFonsecaJ, et al.Aeroelastic tailoring using fiber orientation and topology optimization. Struct Multidiscip Optim2012; 46: 663–677.
19.
KatsikadelisJBabouskosN. Optimum design of thick laminated anisotropic plates via frequency regulation. A BEM approach. In: Advances in mechanics of materials and structural analysis: in honor of Reinhold Kienzler. Cham: Springer, 2018, pp. 223–239.
20.
VijayBDurvasulaS. Supersonic flutter of composite skin panels of repeated-sublaminate layup. Compos Struct1998; 41: 121–135.
21.
BendsoeMPSigmundO. Topology optimization: theory, methods, and applications. Springer Science and Business Media, 2013.
22.
OsanovMGuestJK. Topology optimization for architected materials design. Annu Rev Mater Res2016; 46: 211–233.
23.
BendsoeMPKikuchiN. Generating optimal topologies in structural design using a homogenization method. Comput Methods Appl Mech Eng1988; 71: 197–224.
24.
StanfordBBeranP. Optimal structural topology of a platelike wing for subsonic aeroelastic stability. J Aircraft2011; 48: 1193–1203.
25.
StanfordBBeranP. Aerothermoelastic topology optimization with flutter and buckling metrics. Struct Multidiscip Optim2013; 48: 149–171.
26.
FerrariFSigmundO. A new generation 99 line Matlab code for compliance topology optimization and its extension to 3D. Struct Multidiscip Optim2020; 62: 2211–2228.
27.
AndreassenEClausenASchevenelsM, et al.Efficient topology optimization in MATLAB using 88 lines of code. Struct Multidiscip Optim2011; 43: 1–16.
28.
FerreiraA. Analysis of composite plates using a layerwise theory and multiquadrics discretization. Mech Adv Mater Struct2005; 12(No. 2): 99–112.
29.
Bismarck-NasrMN. Finite element analysis of aeroelasticity of plates and shells. Appl Mech Rev1992; 45: 461–482.
30.
MarquesFDNatarajanSFerreiraAJ. Evolutionary-based aeroelastic tailoring of stiffened laminate composite panels in supersonic flow regime. Compos Struct2017; 167: 30–37.
31.
BartolozziGBaldanziniNPieriniM. Equivalent properties for corrugated cores of sandwich structures: a general analytical method. Compos Struct2014; 108: 736–746.
32.
OmaireySLDunningPDSriramulaS. Development of an ABAQUS plugin tool for periodic RVE homogenisation. Eng Comput2019; 35: 567–577.
33.
ChakrabartiASheikhA. Vibration of laminate-faced sandwich plate by a new refined element. J Aero Eng2004; 17(No. 3): 123–134.
