Structure Design And Error Compensation Of An Aircraft Part Posture Adjustment System

Digital flexible automatically assembly system is using in the process of modern aircraft assembly, which mainly consist of mechanical positioning system, control system, measuring system and computer software, etc.The pose accuracy are the main factors influencing the aircraft assembly quality.But in the actual process of aircraft assembly, Aircraft parts attitude control is base on the kinematics inverse solution, namely given a parts’ theoretic al position to solve each active locator’ drive displacement. The structure parameters design value is used in the process of the kinematics reverse solution. This exist inevitably errors between the actual structure parameters and the design value.the components posture error is larger, parts docking process is easy to cause interference.Combining with Nanjing University of Aeronautics and Astronautics with a domestic airline in the project fuselage and wings assembly, Take the 3-PPPS parallel parts posture adjustment mechanism as the research object. Carried out research in the design and error compensation of the parts posture adjustment mechanism, for the purpose of improve the accuracy and efficiency of the parallel parts posture adjustment mechanism To avoid the interference in the process of wing and body docking.the main research content is as follows:1) Analysis error factors which effect in the process of the parts’ posture ajust and docking, and on the basis of the structure error of the part’ posture mechanism, get the wing position error structure model in the docking process.2) According to the characteristics of the parallel parts docking mechanisms structure, with three servo displacements as the breakthrough point, establish the ball joint position constraint equation, by solving the theoretical positioning of the ball joint, to give a closed-form highly efficient institutions pose positive solution form of solution. with a laser tracker, identify the part posture adjustment mechanism structure parameter error. Through revise the locator displacement to compensation the error.3) Design aircraft parts posture adjustment simulation mechanism, according to the design index, calculates the locator main structural parameters, based on the finite element software ABAQUS to check parts strength.Base on laser tracker’s own SDK development a data measurement software.Using a single Leica AT901-MR to conduct the complete error compensation experiment on the aircraft parts posture adjustment simulation mechanism.