This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Refined Preliminary Weight Estimation Tool for Airplane Wing and Tail
Technical Paper
2011-01-2765
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
This paper presents the functionality of a new software tool for the preliminary estimation of wing and tail weight, based on a quasi-analytical structural sizing method. The implemented method is based on the weight decomposition of each lifting surface into primary and secondary contributions. The primary weight of both wing and tail empennages is estimated by stationary sizing of the torque box structure, based on tension and compression stress analysis of stiffened panels for the lower and upper surfaces, and shear stress analysis for the spar webs. Aerodynamic loads are calculated by a vortex lattice method for various load cases, as specified by airworthiness regulations. Inertial reliefs on loads due to the mass of the lifting surface structure, fuel and engine are taken into account, as well as the weight penalties due to engine mounting, connections and aeroelastic effects at high speeds. The weight estimation of the secondary structure (fixed leading and trailing edges, flaps, etc.) is based on the use of empirical relations. Some coefficients have been defined to allow designers investigating the effect of new materials and manufacturing techniques on weight. The tool includes a parametric geometry model able to swiftly generate dedicated models both for the aerodynamic and structure solvers. As a result, proper aerodynamic load distributions can be generated very quickly for the structural analysis of any generic lifting surface. Hence, much more accurate results can be achieved than with any other existing class II weight estimation methods, yet with a computational time much shorter than using more sophisticated methods based on finite element analysis. The tool has been validated for a limited number of passenger aircraft including one regional twin turboprop, and a few medium and long range turbofan airplanes. The result of the weight prediction is outstanding, with an average error of 1% for both wing and tail components.
Authors
Citation
Elham, A., La Rocca, G., and Vos, R., "Refined Preliminary Weight Estimation Tool for Airplane Wing and Tail," SAE Technical Paper 2011-01-2765, 2011, https://doi.org/10.4271/2011-01-2765.Also In
References
- Roskam, J. “Airplane Design Part I” DAR corporation Kansas 1985
- Torenbeek, E. “Synthesis of Subsonic Airplane Design” Delft University Press Delft 1985
- Raymer, D. “Aircraft Design, a Conceptual Approach” Washington D.C. 1992
- Howe, D. “Aircraft Conceptual Design Synthesis” Professional Engineering Publishing London 2000
- Bindolino, G. Ghiringhelli, G. Ricci, S. Terraneo, M. “Multilevel Structural Optimization for Preliminary Wing-Box Weight Estimation” Journal of Aircraft 47 2 March April 2010
- Laban, M. Arendsen, P. Rouwhorst, W. F. J. A. Vankan, W. J. “A Computational Design Engine for Multidisciplinary Optimisation with Application to a Blended Wing Body Configuration” 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimisation Atlanta 2002
- Burt, M.E. “Weight Prediction for Wings of Box Construction” RAE Report, No. structure 186 1955
- Shanley, F.R. “Weight-Strength analysis of Aircraft Structures” Dover Publication Inc. New York 1960
- Torenbeek, E. “Development and Application of a Comprehensive, Design-sensitive Weight Prediction Model for Wing Structures of Transport Category Aircraft” Report LR-693 Delft University of Technology September 1992
- Macci, S.H. “Semi-Analytical Method for Predicting Wing Structural Mass” SAWE Paper No 2285 May 1995
- van Dijk, G.J. “Development of a Wing Weight Prediction Method” Haarlem Institute of Technology Haarlem May 1987
- Terpstra, A. “Wing Weight Prediction in the Preliminary Design Phase” Master of Science Thesis Delft University of Technology November 2002
- Kelm, R. Lapple, M. Grabietz, M. “Wing Primary Structure Weight Estimation of Transport Aircrafts in the Pre-Development Phase” SAWE Paper No. 2283 May 1995
- European Aviation Safety Agency “Certification Specifications for Large Aeroplanes CS-25” Amendment 9 5 August 2010
- La Rocca, G. van Tooren, M. J. L. “Knowledge-Based Engineering Approach to Support Aircraft Multidisciplinary Design and Optimization” Journal of Aircraft 46-6 2009
- Kulfan, B.M. “A Universal Parametric Geometry Representation Method - CST” AIAA Paper 07-0062 Reno, NV Jan. 2007
- Verhoff, A. Stooksberry, D. Cain, A.B. “An Efficient Approach to Optimal Aerodynamic Design Part I: Analytical Geometry and Aerodynamic Sensitivities” AIAA Paper 93-0099 Jan. 1993
- Drela, M. Youngren, h. “AVL 3.26 User Primer” 2006
- Niu, M.C.Y. “Airframe Stress Analysis and Sizing” Hong Kong Conmilit Press Ltd. Hong Kong 1997