翼身融合民机典型PRSEUS受压壁板屈曲及渐进损伤分析

Due to the excellent loading advantage of stability under compression and damage arrest/crack arrest, the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS), put forward by NASA and the Boeing Company, has become the major solution to solve low efficiency and poor stability problems caused by non-circular fuselage cross section in civil aircraft. This paper carries out linear/nonlinear buckling and progressive damage analysis for representative compressed PRSEUS panel structure. The methods of modeling the geometric relationship of the support configuration and offset reference surface of skin, tears-trap, stringer flange, frame flange integrated stitched supporting configuration are put forward, improving the accuracy of the finite element model of PRSEUS compressed panel. A mesh convergence analysis method that takes buckling eigenvalue, nonlinear buckling load and other factors into account is proposed to improve the computational efficiency of PRSEUS compressed panel buckling analysis. Three initial imperfection introduction methods including the minimum buckling eigenvalue, geometrical node offset, and combination of the minimum buckling eigenvalue and geometrical node offset are presented to improve the calculation accuracy of the finite element model of PRSEUS compressed panel. Finally, the nonlinear buckling progressive damage analyses of representative PRSEUS compressed panel based on the damage constitutive relation between fiber and matrix are completed. By comparing the experimental results, the nonlinear buckling progressive damage evolution analysis methods for PRSEUS structure are presented. This paper provides the methods and technical support for the stability/damage analysis and design of the PRSEUS structure in blended-wing-body civil aircraft.