Tolerance Analysis Method of Aircraft Door Sealing Structure Based on Linear Simplified Model

As a moving component of the aircraft, the sealing state of the door will directly affect the aircraft's pressurization level and aerodynamic performance. The existing analysis methods of sealing structures mainly consider the compression deformation and contact stress of the seals. However, in practical engineering applications, it has been found that the sealing performance of cabin door depends on the interaction between the sealing structure and the seal. On the one hand, the tolerance fluctuation and elastic deformation of the sealing structure will cause the deviation between the actual compression ratio of the seal from the theoretical value; On the other hand, the deformation caused by the resilience of the seal will change the tolerance distribution of the sealing structure. In this paper, based on the local linear simplification of loading curve of the seal, the calculation efficiency of the large-size sealing structure’s deformation is improved, so that the compression ratio fluctuation of the seal is converted into the deformation tolerance which is included in the tolerance simulation of the sealing structures to obtain the distribution characteristics of step difference value on the aerodynamic surface as well as the different compression states of the seal. The validity of this analysis method is confirmed by comparing with the commercial software calculation and the practical measured data of the aircraft door.