The design process is no longer a trial-and-error procedure due to the introduction of computer-aided tools and optimization techniques. The product development process is therefore accelerated, allowing to produce more in a relatively lesser time. Moreover, the best possible design, with regard to the performance, can hence be obtained. When applied to the design of an aircraft wing, the optimization objective is usually to minimize the structural weight under failure-based constraints. This paper presents an optimization strategy that allows the determination of the wing surface structural thicknesses corresponding to the minimal weight while keeping the structure safe in terms of strength and buckling. This strategy is applied for the wing sizing process of a new two-seater very light aircraft, currently under development. The design process goes through geometric modeling, aerodynamic calculations using vortex lattice method, and finite element modeling. Structural optimization is performed within MATLAB, and is based on the automatic execution of the finite element solver MSC.NASTRAN.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Structural sizing for the weight estimation of a very light aircraft wing


    Contributors:


    Publication date :

    2018-11-01


    Size :

    7 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Aircraft wing weight estimation

    Carreyette, J.F. | Engineering Index Backfile | 1950


    Aircraft Wing Weight Estimation

    Carreyette, J.F. | Emerald Group Publishing | 1950


    Structural Sizing for Weight Estimation in Preliminary Aircraft Design

    Wenzel, J. / Society of Allied Weight Engineers | British Library Conference Proceedings | 2007