<p>Aircraft icing remains one of the major problems in flight control and operation of aircraft. To avoid ice accretion various de-icing and anti-icing approaches have been developed. Recently, advanced studies were performed in the fields of numerical modeling of ice accretion, and its melting during an application of de-icing and anti-icing systems. However, little attention is still paid to the thermomechanical response of aircraft composite structures acting under icing conditions and using de-icing systems. The results of numerical simulations on thermomechanical response of a representative composite aircraft skin were analyzed, emphasizing representative scenarios of aircraft icing and acting of resistive heaters as a de-icing system. A detailed introduction to energy and mass transfer of ice accretion and melting phenomena was described to highlight additional major thermal effects. A comparative analysis between wet and dry air conditions was carried out. The simulations of aero-thermodynamic and structural coupling phenomena performed demonstrated mechanical behavior of composite aircraft structures under these complex conditions.</p>