Loading...

Aeroservoelastic stability of supersonic slender-body flight vehicles

Haddadpour, H ; Sharif University of Technology | 2006

244 Viewed
  1. Type of Document: Article
  2. DOI: 10.2514/1.13591
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2006
  4. Abstract:
  5. An analytical procedure for aeroservoplastic stability analysis of guided supersonic flight vehicles is developed by using slender body aerodynamic theory and modal analysis techniques. The roll channel is decoupled from pitch and yaw channels by using the linearized system of equations. Results show that divergence is the only aeroelastic instability that can occur for the nonrolling flight vehicle with no-control loop and is accurately computed using the first bending mode shape. The result of the divergence analysis demonstrates that the vehicle elasticity has a destabilizing effect on the pitch and yaw channels. The inclusion of aeroservoelasticity in the analysis can cause dynamic instability, even if the guided rigid vehicles is also stable in no-control loop flight. This type of instability can be controlled by some parameter adjustments in the control system, while the control system gain variation does not affect the static divergence dynamic pressure and flutter frequency
  6. Keywords:
  7. Aerodynamics ; Aircraft ; Elasticity ; Gain control ; Supersonic flow ; Aerodynamic theory ; Divergence analysis ; Roll channels ; Flight dynamics
  8. Source: Journal of Guidance, Control, and Dynamics ; Volume 29, Issue 6 , 2006 , Pages 1423-1427 ; 07315090 (ISSN)
  9. URL: https://arc.aiaa.org/doi/abs/10.2514/1.13591?journalCode=jgcd