A design-oriented analysis capability for aircraft fuselage structures that utilizes equivalent plate methodology is described. This new capability is implemented as an addition to the existing wing analysis procedure in the Equivalent Laminated Plate Solution (ELAPS) computer code. The wing and fuselage analyses are combined to model entire airframes. The paper focuses on the fuselage model definition, the associated analytical formulation and the approach used to couple the wing and fuselage analyses. The modeling approach used to minimize the amount of preparation of input data by the user and to facilitate the making of design changes is described. The fuselage analysis is based on ring and shell equations but the procedure is formulated to be analogous to that used for plates in order to take advantage of the existing code in ELAPS. Connector springs are used to couple the wing and fuselage models.
Design-Oriented Analysis of Aircraft Fuselage Structures
2004
18 pages
Report
Keine Angabe
Englisch
Design-Oriented Analysis of Aircraft Fuselage Structures
NTRS | 1998
|Design-oriented analysis of aircraft fuselage structures
AIAA | 1998
|Design-oriented Analysis of Aircraft Fuselage Structures
British Library Conference Proceedings | 1998
|