Abstract
A generalized direct simulation method using a discrete time-domain state-space approach for transient response of both open and closed-loop nonlinear aeroelastic systems is developed. Based on a nonlinear parameter scheme that divides the nonlinear system into sub-linear systems, the present method first assembles a set of discrete time-domain state-space equations and then computes the transient response by switching the time-integration procedure between this set of state-space equations. In so doing, various nonlinearities in structures, aerodynamics and/or control systems can be included. The present method is validated by correlating the transient response of a three-degree-of-freedom airfoil section in freeplay with the experimental and numerical results obtained by Conner et al. The stability of a strut-braced wing with buckling effects at two trim conditions is also studied, which shows that the aeroelastic stability of the present strut-braced wing is trim-condition dependent. Such results clearly could not be obtained if using a linear aeroelastic analysis.
| Original language | English |
|---|---|
| Pages (from-to) | 3064-3074 |
| Number of pages | 11 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 4 |
| 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