Material Selection for a Curved C-Spar Based on Cost Optimization
2011 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 48, no 3, 797-804 p.Article in journal (Refereed) Published
A case study for the cost optimization of aircraft structures based on the operating cost as an objective function is presented. The proposed optimization framework contains modules for estimation of the weight, manufacturing cost, nondestructive inspection cost, and structural performance; the latter is enhanced by a kinematic draping model that allows the fiber angles to be simulated more realistically. The case study includes five material systems: aircraft-grade aluminum, two types of resin-transfer molded noncrimp fabric reinforcements, and two types of M21/T800 prepreg. The results are compared in relation to each other, and it is shown that (depending on the estimated fuel burn share of the component) a different material system is favorable when optimizing for low-operating cost.
Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics, 2011. Vol. 48, no 3, 797-804 p.
COST/WEIGHT OPTIMIZATION, COMPRESSIVE STRENGTH, AIRCRAFT STRUCTURES, FUSELAGE FRAMES, WEIGHT DESIGN, MINIMUM-COST, PERFORMANCE, COMPOSITES, PANELS, PART
Engineering and Technology
IdentifiersURN: urn:nbn:se:kth:diva-39049DOI: 10.2514/1.C000188ISI: 000291574700008ScopusID: 2-s2.0-79958017017OAI: oai:DiVA.org:kth-39049DiVA: diva2:439394
FunderTrenOp, Transport Research Environment with Novel Perspectives
QC 201109072011-09-072011-09-072015-09-29Bibliographically approved