Aircraft Adjustment And Error Evaluation Based On Deformation Compensation

The plane shape of siding and other large parts of j oint quality directly affects the aircraft's aerodynamic shape,reliability,security and performance,which is of critical importance to the overall quality of the aircraft.Aircraft digital assembly,automatic docking panel component assembly can effectively improve the quality and efficiency of the aircraft,but the the strength of the large aircraft panel is weak,and easy to deformation,if the choice of the measuring point is seriously deformed,it will greatly affect the panel pose fitting,pose adjustment of the whole component will not be able to meet the requirements of the project.The deformation of components have become the biggest challenge in automatic docking and digital measurement.The thesis is based on fuselage models in a panel assembly to analysis the measurement difference,deformation caused by fitting error and some other factors influencing the quality of panel assembly,to put forward the pose evaluation model,pose uncertainty evaluation model in order to achieve the quantified formulation of product deformation-position change.Applying to finite element analysis for side wall,the top wall panel deformation under the constraints of its own gravity and work provide the basis for the development of the measurement scheme and put forward the measured error evaluation method.Through the analysis of micro deformation process of the large wall panel assembly,with reference to the results of finite element analysis,the thesis introduce the deformation of the weight factor,optimize traditional singular value decomposition algorithm in order to form the pose fitting optimization algorithm based on the deformation compensation.For an example of fuselage panel,test the assembly application,analyze and compare adjusting results of different measurement points.The posture adjustment algorithm in compensation before and after optimization are analyzed and compared.