Imperial College London
Portrait Picture

Professor Rob Hewson

Faculty of Engineering, Department of Aeronautics

Professor of Multidisciplinary Design Optimisation
 
 
 
//

Contact

 

r.hewson Website

 
 
//

Location

 

341City and Guilds BuildingSouth Kensington Campus

//

Summary

 

Publications

Citation

BibTex format

@article{Bach:2016:10.1007/s00158-016-1477-3,
author = {Bach, C and Jebari, R and Viti, A and Hewson, RW},
doi = {10.1007/s00158-016-1477-3},
journal = {Structural and Multidisciplinary Optimization},
pages = {105--119},
title = {Composite stacking sequence optimization for aeroelastically tailored forward-swept wings},
url = {http://dx.doi.org/10.1007/s00158-016-1477-3},
volume = {55},
year = {2016}
}
Download

RIS format (EndNote, RefMan)

TY  - JOUR
AB  - A method for stacking sequence optimization and aeroelastic tailoring of forward-swept composite wings is presented. It exploits bend-twist coupling to mitigate aeroelastic divergence. The method is intended for estimating possible weight savings in preliminary aircraft design stages. A structural beam model of the composite wingbox is derived from anisotropic shell theory and the governing aeroelastic equations are presented for a spanwise discretized forward swept wing. Optimization of the system to reduce wing mass is undertaken for sweep angles of -35 degrees to 0 degrees and Mach numbers from 0.7 to 0.9. A subset of lamination parameters (LPs) and the number of laminate plies in each pre-defined direction (restricted to0, +/-45 and 90 degrees}) serve as design variables. A bi-level hybrid optimization approach is employed, making use of a genetic algorithm (GA) and a subsequent gradient-based optimizer. Constraints are implemented to match lift requirements and prevent aeroelastic divergence, excessive deformations, airfoil stalling and structural failure. A permutation GA is then used to match specific composite ply stacking sequences to the optimum design variables with a limited number of manufacturing constraints considered for demonstration purposes. The optimization results in positive bend-twist coupling and a reduced structural mass. Results are compared to an uncoupled reference wing with quasi-isotropic layups and with panel thickness alone the design variables. For a typical geometry and a forward sweep of -25 degrees at Mach 0.7, a wingbox mass reduction of 13% was achieved.
AU  - Bach,C
AU  - Jebari,R
AU  - Viti,A
AU  - Hewson,RW
DO  - 10.1007/s00158-016-1477-3
EP  - 119
PY  - 2016///
SN  - 1615-1488
SP  - 105
TI  - Composite stacking sequence optimization for aeroelastically tailored forward-swept wings
T2  - Structural and Multidisciplinary Optimization
UR  - http://dx.doi.org/10.1007/s00158-016-1477-3
UR  - http://hdl.handle.net/10044/1/31237
VL  - 55
ER  -
Download