Implementation of reengineering technology to reduce the terms of the technical preparation of manufacturing of aviation technology assemblies

Abstract

The object of this study is the technical preparation of manufacturing (TPM) of aviation technology (AT) using reengineering technology. The task to reduce the terms of TPM AT was tackled while solving direct and inverse problems of shape formation involving reengineering. The study is based on the equation for calculating the labor intensity of creating an assembly unit (AU) as a mathematical model for the formation and accumulation of components of the total labor intensity at all stages. The following results are reported: a scheme has been proposed for linking homogeneous components of an article obtained using the loft-template method (LTM) with digital mock-up (DMU) when applying the reengineering method. The scheme summarizes and structures the reengineering technology to solve direct and inverse shape-formation problems and could be used to solve the tasks of prototyping, manufacturing, and refurbishment of tooling, as well as article control at all stages of production. An example of the helicopter stabilizer shows that when solving the direct shape-formation problem, the labor intensity is from 294.94 to 315.06 man-hours, and when solving the inverse problem ‒ from 194.78 to 213.22 man-hours. A comparative analysis of the labor intensity of TPM revealed a difference of 1.5 times in favor of the labor intensity of solving the inverse problem. Comparing the labor intensity of creating DMU for the stabilizer of a helicopter has made it possible to establish that the labor intensity of solving the inverse problem is 3.7 times less than the labor intensity of solving a direct problem. Recommendations for reducing the terms of TPM AT with the use of reengineering are given. The results could be used to assess the labor intensity and timing of TPM AT and mechanical engineering objects in general when using reengineering technology