Abstract
Previous investigations on a strut-braced wing analysis revealed that aeroelasticity plays an important role on the strut-braced wing design. The investigations showed that the location of the strut support on the wing affects the wing deformation, aerodynamic load redistribution and flutter speed. Another study on the buckling analysis of the strut-braced wing indicated also that the wing stiffness may have a significantly lower stiffness due to the compressive force due to the strut during a positive flight load maneuver. In the present work, a further investigation on the effect of compressive force on flutter and divergence speeds of the strut-braced wing is presented. To reduce the computational time, an efficient non-uniform beam finite element model is used for the wing structure, and a modified doublet lattice method is used for the unsteady aerodynamic calculations. Variation of several parameters, including strut location along the wing spanwise and chordwise directions, were investigated. To calculate the compressive force, a trim analysis was performed for each variation of these parameters. Comparison between the flutter boundary and flight envelope of the present strut braced wing design indicates that the influence of the compressive force on flutter speed is significant when the strut is placed near the wing tip.
| Original language | English |
|---|---|
| Pages (from-to) | 4937-4947 |
| Number of pages | 11 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 7 |
| Publication status | Published - 2003 |
| Externally published | Yes |
| Event | 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Norfolk, VA, United States Duration: Apr 7 2003 → Apr 10 2003 |
ASJC Scopus subject areas
- Architecture
- General Materials Science
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering