Advances in aircraft and spacecraft science

  • 제9권3호
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  • Pages.263-278
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  • 2022
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Dynamic modeling and structural reliability of an aeroelastic launch vehicle

  • Pourtakdoust, Seid H. (Center for Research and Development in Space Science and Technology, Sharif University of Technology) ;
  • Khodabaksh, A.H. (Center for Research and Development in Space Science and Technology, Sharif University of Technology)
  • 투고 : 2021.06.27
  • 심사 : 2022.06.10
  • 발행 : 2022.05.25
⟨ 이전 논문 다음 논문 ⟩

초록

The time-varying structural reliability of an aeroelastic launch vehicle subjected to stochastic parameters is investigated. The launch vehicle structure is under the combined action of several stochastic loads that include aerodynamics, thrust as well as internal combustion pressure. The launch vehicle's main body structural flexibility is modeled via the normal mode shapes of a free-free Euler beam, where the aerodynamic loadings on the vehicle are due to force on each incremental section of the vehicle. The rigid and elastic coupled nonlinear equations of motion are derived following the Lagrangian approach that results in a complete aeroelastic simulation for the prediction of the instantaneous launch vehicle rigid-body motion as well as the body elastic deformations. Reliability analysis has been performed based on two distinct limit state functions, defined as the maximum launch vehicle tip elastic deformation and also the maximum allowable stress occurring along the launch vehicle total length. In this fashion, the time-dependent reliability problem can be converted into an equivalent time-invariant reliability problem. Subsequently, the first-order reliability method, as well as the Monte Carlo simulation schemes, are employed to determine and verify the aeroelastic launch vehicle dynamic failure probability for a given flight time.

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