Cross-sectional cutaway illustration of a solid rocket motor (SRM) during firing. The casing is cut open along the longitudinal axis to reveal the internal combustion chamber. The solid propellant grain is partially burned, exposing a star-shaped or cylindrical port geometry. Hot combustion gases flow axially from the burning propellant surface toward a converging-diverging nozzle on the right, visualized through color gradients (deep orange/red near the flame front transitioning to bright yellow toward the nozzle throat). Velocity streamlines or flow arrows show the 1D axial gas flow along the chamber axis. The nozzle throat and exit are clearly visible. Technical, engineering illustration style with clean lines, slight glow effects on the flame and gas flow, dark background. No text, no labels. Ver más