Nowadays

for the requirement of developing automation in the process of aircraft manufacturing

higher requirements are placed on the assembly accuracy

methods

space occupancy

control mode and personal safety of the various components of the aircraft. Due to the assembly work

it has become one of the vital problems to be solved that large parts of the aircraft can’t change their position automatically. Traditional position-changing modes have problems such as inefficient use

large space occupation

operational difficulties and safety hazards

which make it impossible to meet the production requirements of modern aviation manufacturing industry

so there is an urgent need for improvement and innovation. In this paper

requirements of the automatic position-changing of the wing parts are taken as the research content. First

the structural characteristics and position-changing requirements of the wing parts are analyzed. Then

combined with the principle of the crank slider mechanism

a new automatic position-changing system and control system are designed. At last

based on the finite element analysis method

the MSC. Patran Nastran engineering software is used to perform the strength calculation on the main load-bearing structure to meet the demand of the secure and reliable automatic position-changing of the wing parts.