ОСОБЛИВОСТІ СКЛАДАННЯ ПЛАНЕРІВ ЛІТАКІВ, ЯКІ МІСТЯТЬ ЕЛЕМЕНТИ ІЗ КОМПОЗИЦІЙНИХ МАТЕ-РІАЛІВ

Abstract

The results of the analysis of the possibility of using known methods for assembling the components of an aircraft airframe, containing, in particular, elements of composite materials (CM), are presented. The features of structures made of CM and their joints, which affect the subsequent assembly of such structures, are considered. Systematized information about the terminology in the home area. Alternative formulations of assembly-related terms are proposed.Some features of the choice of methods for assembling structures containing elements from CM are considered. The properties of CM that influence the choice of assembly bases are analyzed. Potentially possible bases for assembling components of aircraft structures from CM, as well as CM and metals in different proportions, in particular, the method of assembly using virtual bases, are proposed. The classification of methods for assembling aircraft all-metal structures is carried out, technological limitations of CM are indicated, which have a direct impact on the use of the corresponding elements of assembly equipment. Some cases of imitation of design solutions of aircraft structures made of metals into structures containing elements of CM are considered. The typification of the main assembly units of the airframe of the aircraft has been made, in terms of orientation to certain assembly methods.Formulas for calculating the value of the total error in the assembly of components made of metals are proposed. The factors influencing the magnitude of the total error for CM structures are substantiated. The current trends in the use of CM at the SE «ANTONOV» are formulated in an enlarged way. An adaptive scheme for choosing a method for assembling assembly units containing, in particular, elements from CM, obtained by extrapolation from all-metal structures, has been developed.Conclusions are drawn about the need to orient the developed aircraft structure to a certain assembly method, and the main conditions for carrying out assembly work on composite parts from CM are formulated. The possibility of assembling aircraft structures from CM, as well as CM and metals in different proportions, with predominantly based on holes using simple assembly equipment, has been determined.