MODELING OF THE FRAME STRENGTH OF THE MISSILE AND BOMBING GEAR OF THE Мi-8МСБ-В HELICOPTER IN THE TEST PROCESS

Abstract

The problem of ensuring the frame strength of missile and bombing gear of the Ми-8МСБ-В helicopter pylon in the course of testing is considered. The methods of calculation of the frame strength at maximum load are developed to solve this problem; as well as modeling of design for the main operating modes of the helicopter is conducted.
 Previously, on the basis of force factors the loading coefficients of the helicopter on its operational modes are determined, particularly in combat use (dive with a volley of missiles and bombing).
 While conducting modeling the advanced methods of calculating the design of the frame strength parameters were applied, i.e. the analytical manual calculation and computational programs of computer-aided design (CAD). Manually calculating the forces and stresses in the framework (using cut nodes) the frame was idealized as rod model with hinged connections of the elements in the nodes A system of equations for each node was formed, which were solved in MathCAD. In the automated calculation of forces and stresses in the design of the frame the finite element method was implemented, which is used in WinMachine programs and SolidWorks Modeling.
 The mathematical modeling of the frame was made at the maximum anticipated in-flight loads for determination the critical force and the maximum stress in the construction elements. In addition, the analysis for the redundant deformation was carried out.
 Performed calculations, mathematical and simulation modelling proved that the necessary strength requirements are met for all the elements of the frame under its maximum load in all flight operational modes.