Research On The Lightweight Technology Of A Helicopter Fuselage With The Tail Drive System

Helicopter is an important part of the aircraft.It has many advantages,such as light and flexible,vertical take-off and landing,hovering in the air,super low altitude flight,forwards,backwards and sideways flight in either direction.These advantages make it very extensive application in the national economy and national defense.Helicopter technology has become an important indicator of a country's scientific and technological strength.In helicopter manufacturing industry increasingly fierce competition today,how to use the shortest time to design a better structure,lighter weight,higher performance,energy-saving economy,comfort and safety of the helicopter has become placed in front of the helicopter manufacturer must face a new challenge and the structure lightweight design is the premise and foundation of this a series of important indicators.In the field of helicopter development,lightweight design has become one of the main directions of the design.Lightweight design will save the use of material,reduce the weight of the body and reduce carbon emissions.This paper establishes the finite element cell model of helicopter fuselage to for the static and dynamic analysis of study on the helicopter fuselage.With FURIA light helicopter fuselage as the research object,using ANSYS to establish the finite element cell model of helicopter fuselage to study the helicopter fuselage modeling process;Secondly,we analyze the static characteristics and dynamic characteristics of a helicopter fuselage in-depth research to analysis and evaluation of the helicopter fuselage performance.With the take-off condition,flying condition and landing conditions of static analysis,it is concluded that the helicopter fuselage under three conditions of stress concentration area and maximum displacement deformation position,and evaluates the strength and stiffness of the helicopter fuselage.Extracting the 7 to 22 order free modal of helicopter fuselage,we receive all orders of modal frequencies and mode shapes.The harmonic response analysis verifies the results of modal analysis.The analysis results show that the stiffness and strength satisfy the helicopter fuselage usage requirement,at the same time inherent frequency is also meet the requirement and helicopter fuselage has large lightweight potential,Thirdly,with helicopter fuselage each section of the beam pipe sizes as design variables and the volume of the helicopter fuselage as the aim to design,building the finite element optimization model of helicopter fuselage and carrying on the preliminary discussion on helicopter fuselage lightweight design with theANSYS optimization module.Getting the optimized optimal each section size and minimum volume of fuselage.Studying the static analysis and modal analysis for optimized finite element model to compare of results before and after.optimization.The results show that the optimized body quality deecreased by 29.31%than before optimization.So the helicopter fuselage structure optimization makes fuselage vibration natural frequency level decreases to a certain extent at the same time achieved the purpose of lightweight,the performance and quality have no effect on the.fuselage.Thus for the similar aircraft structure lightweight approach provides a reference.