Finite-element modeling of the heat mode of autoclave hardening of a three-layer panel

Results of finite-element modeling and experimental measurements of temperatures in the course of autoclave hardening of a three-layer panel of the wing of a T-50 aircraft, which is composed of upper and lower load-bearing panels made of carbon plastics and honeycomb from aluminum foil, are given. It is shown that the actual temperature values at various sections of the panel of wing differ from the theoretical ones by less than 90%.