Due to its excellent property

the application amount of composite materials on the new generation airframe has gradually increased. As a result

it’s of vital importance to improve the quality of assembly process and reduce the stress during assembly process. However

composite components have different characteristics from traditional metal structures. They are large in scale

nonrigid

easy to deform due to its own weight

and with large manufacture deviation. Moreover

they are easy to be damaged when confronted forced assembly. In order to meet the requirements of composite structures during assembly process

new technologies and methods need to be developed. This research takes the Airbus A320 wing box model as an example

states the typical assembly process of composite aircraft structure

and points out some problems in the process

such as high dependence on engineering experience

difficulty in prediction of gaps

and weak ability of shape adjusting; to solve those questions

three kinds of new airframe assembly technology were developed

which are assembly simulation technologies for tolerance control of composite structures

online control technology for assembling deformation of aircraft composite panels and effect of assembling deformation of cladding panel on service performance. At last

the shortcomings and the prospects in assembly deformation control technology of aircraft composite panel are pointed out.