Aerospace Instrument-Making Annotation << Back Optimal design of composite shells of type shell compartment of the aircraft at the complex-temperature and force loading Larichev E.A. Safronov V.S. The article presents the model and method of optimal design of composite shell type shell compartment of the aircraft at the complex thermo static and dynamic loading. As a method for optimizing the selected modified gradient projection method. Variable parameters have been selected: the number of layers of the shell and the winding angle fiberglass. Formulation Engineering Design task is to choose the optimal variant design and technological solutions and determine the design parameters of cylindrical composite shell by minimizing the weight of the considered structure. As a result of optimization procedures derived design parameters depending on the parameters of the outer shell thermo loading. It is shown that an increase in the external pressure, axial compression, increase the value of design parameters, and as a result, increases and the mass of the shell. Key words: composite shell, integrated thermal loading, optimum designing, gradient method. Contacts: E-mail: v.s.safronov@mail.ru Pp. 22-27.