Feasibility of a Morphing Rocket Nozzle for Thrust Vector Control based on Corrugated Composite Laminates

Abstract The paper presents technological, experimental and numerical studies aimed at the development of a morphing nozzle in composite material with deformable divergent section, which is designed to control vector thrust rockets without using mechanisms or localized flexible joints. design characterized by corrugated walls longitudinal elements that make possible separation load paths involved bending response, bearing internal pressures related force resultants. Mechanical requirements conditions pressure, temperature gas velocity part are defined selecting investigating two potential application scenarios. Thereafter, both technological aspects assessment mechanical performances addressed designing, manufacturing testing demonstrator capabilities. A lightweight thermal protection system proposed, numerically analyzed. Finally, virtual developed. Results point out possibility axial capability may undergo significant deformation failures. integration systems leads promising concept for innovative rocket engine applications.