BibTeX:

@article{IJIRSTV4I1068,
     title={Maneuver Load computation using Static Aeroelastic Phenomena for a Typical Subsonic Aircraft},
     author={Veeresha G, Dr. M S Ganesha Prasad, Girish S and Dr. Manjunath},
     journal={International Journal for Innovative Research in Science & Technology},
     volume={4},
     number={1},
     pages={178--182},
     year={},
     url={http://www.ijirst.org/articles/IJIRSTV4I1068.pdf},
     publisher={IJIRST (International Journal for Innovative Research in Science & Technology)},
}

Maneuver Load computation is a very important task of any design process for an aircraft industry. The field of flight loads computation is concerned with the provision of loads due to maneuvering flight. Hereby, the underlying simulation model consists of a model for the flexible subsonic aircraft. The analysis will be performed for a variety of flight points and load cases. It consists of maximum structural loads over the airframe due to prescribed maneuvers like symmetric NZ The goal of the current work is it to compute maneuver load using static aeroelastic phenomena on a typical subsonic aircraft for sizing the primary structures like Wing, Fuselage, Horizontal and Vertical stabilizers. The FE Modeling will be done in HYPERMESH and the flight load module of the MSC/PATRAN will be used for aero mesh generation. The static aeroelastic module of the MSC/NASTRAN is used as the solver. The shear force and bending moment diagram will be plotted for fuselage, wing, HT, and controlling surface about their respective elastic axis in PATRAN.

Static Aeroelastic, Hypermesh, Patran, Nastran