Aeroelastic Analysis of Pinched Panels in Supersonic Flow Changing with Altitude

Abstract

An analysis of panel flutter phenomena for panels supported by a fixed number of pinched points and exposed to flow conditions that vary with altitude is reported in this paper. This is the case of so-called thermal insulation panels attached to space launcher tanks for which no results have been found in the open literature. Because piston theory has been used for the flow, attention has been limited to supersonic flows. The structural model is based on a refined one-dimensional variable kinematic theory, which has been recently proposed by the authors. The aeroelastic governing equations have been written in matrix form by employing finite element methods. These methods are very appropriated for pinched boundary conditions considered herein. Various numbers of attachment points have been considered as well as simply supported cases. A flutter boundary has been established for various flat panels and flow conditions.