@Article{icces.2023.010490,
AUTHOR = {Dan Xie, Shihao Zhang, Zijun	Yi},
TITLE = {Aeroelastic	Analysis	of	Hypersonic	Aircraft	Wing},
JOURNAL = {The International Conference on Computational \& Experimental Engineering and Sciences},
VOLUME = {26},
YEAR = {2023},
NUMBER = {1},
PAGES = {1--1},
URL = {http://www.techscience.com/icces/v26n1/53891},
ISSN = {1933-2815},
ABSTRACT = {Considering	the	high	cost	of	numerical	simulation	for	aeroelastic	coupling	analysis,	it	is	difficult	to	directly	
apply	 it	 to	 engineering.	 In	 this	 paper,	 the	 typical	 swept	 trapezoidal	 wing	 of	 hypersonic	 aircraft [1]	 is	
simplified	to	a	cantilever	trapezoidal	plate [2].	Based	on	semi-analytical	method [3],	including	von	Karman	
plate	theory	to	consider	the	structural	geometric	nonlinearity,	third-order	piston	theory	to	calculate	quasi	
steady	 aerodynamic	 force,	 and	 Rayleigh-Ritz	 method	 to	 characterize	 the	 displacement	 as	 a	 mode	
superposition	form,	the	aeroelastic	equation	of	the	swept	trapezoidal	wing	is	established,	and	the	fourthorder	 Runge	 Kutta	 numerical	 integration	 is	 used	 to	 solve	 the	 aeroelastic	 response,	 realizing	 the	 rapid	
prediction	 of	 the	 stability	 boundary.	 Furthermore,	 by	 changing	 the	 geometric	 parameters	 of	 the	 swept	
trapezoidal	 wing,	 including	 sweep	 angle,	 taper	 ratio	 and	 aspect	 ratio,	 the	 effects	 of	 wing	 geometry	
parameters	on	aeroelastic	response	characteristics	and	flutter	critical	dynamic	pressure	are	studied.},
DOI = {10.32604/icces.2023.010490}
}