Semi-Analytical Weight Estimation Method for Fuselages with Oval Cross-Section

Semi-Analytical Weight Estimation Method for Fuselages with Oval Cross-Section

Vos, R.
Hoogreef, M.F.M.

Aerospace Engineering

Aerodynamics, Wind Energy & Propulsion

2013-04-09

This paper presents a semi-analytical method for the weight estimation of fuselages with an oval cross-section, applied to blended wing body aircraft. The weight estimation of the fuselage primary structure is based on a structural analysis of two-dimensional crosssections and it is completed by a set of empirical relations for the weight estimation of the secondary structure and non-structural items. A conceptual design study on a stable (5% static margin), 400-passenger blended wing body aircraft has been performed with the weight estimation method implemented in an aircraft conceptual-design program. A top level requirement for the harmonic range of 15,200km was imposed on the design. From the anaylis a maximum take-off weight of 395 metric tons has been found, with an operative empty weight fraction of 45% and a fuselage airframe weight of 47.3 metric tons (amounting to 26% of the operative empty weight). The results of this study are presented in comparison to the Boeing 777-200LR airliner, showing a slightly higher operative empty weight fraction, a lower fuel consumption of 2.05kg per passenger per 100km.

blended wing body
oval fuselage
weight estimation
class 2.5 weight estimation
semi-analytical weight estimation

http://resolver.tudelft.nl/uuid:6d961ece-c87e-484f-bf61-7cdb2f93ffd5

https://doi.org/10.2514/6.2013-1719

American Institute of Aeronautics and Astronautics (AIAA)

http://arc.aiaa.org/doi/abs/10.2514/6.2013-1719

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Boston, Massachusetts, 8-11 April 2013; AIAA 2013-1719

Institutional Repository

conference paper

© 2013 by Maurice Hoogreef
Roelof Vos