Case Bond Stress Calculations for Flapped Cylindrical Analogs of Solid Propellant Rocket Motors. Bondline Parametric Studies

摘要

Numerical stress solutions were obtained for finite-length cylinders bonded to a flexible case and subjected to thermal shrinkage, axial acceleration, and internal pressure loading. Finite-element models contained insulator, flap, case-bond liner, and propellant layers typical of solid propellant rocket motors. Grid structure in the region of the flap termination was highly refined to provide accurate estimates for the maximum case-bond stresses. The stress solutions indicated that the flap length, flap modulus, and liner modulus do not significantly affect case-bond stresses. The most important parameter relative to maximum stresses is the thickness of material between the flap-insulator bondline and the liner-propellant bondline. (Author)