Thermal analysis of antiskid aircraft brake system

For a multiple carbon-carbon composite aircraft disk brake system, a transi ent heat transfer analysis is numerically carried out using temperature-dep endent thermophysical properties. Operations of the antiskid control brake system are simulated by considering variations of pressure and angular spee d during the braking action. The heat developed during that process is assu med to be convectively released. Maximum temperatures are found to occur ar ound the middle disk and on the disk mid-radii. Maximum and minimum tempera ture differences amounting to 350 degrees C are found to occur inside the b rake assembly.