Abstract: A hybrid prepreg-resin transfer moulding (Prepreg-RTM) process was proposed to realize the integration manufacturing of composite cross stiffened composite cabin. The rheological properties of prepreg resin (AC631) and RTM resin (6421A) were studied. The results show that the two resin systems have good co-forming processes basis. Combined with cabin structure design, layup design and mould design, the integrated preparation process of composite cross stiffened cabin based on hybrid Prepreg-RTM technology was verified. The results show that the cabin structure has good surface quality, dimensional accuracy and internal quality. The service strength of cabin was verified by static strength tests at room temperature and high temperature, and its failure mechanism and failure mode were studied by high temperature failure test. The results of static strength test at room temperature show that the cabin maintains good structural integrity under 125% service load, and the maximum strain of the cabin is −1283×10⁻⁶ which meets the static strength design requirements. The static strength test results at 100℃ reveal that the maximum strain of the cabin is −1315 ×10⁻⁶. There is no abnormal state such as instability and failure occurred in the cabin, which meets the requirements of thermal-mechanical coupling condition design. The high temperature failure experiment results demonstrated that the cross stiffened composite cabin failed under 143.2% service load at high temperature of 150℃, caused by the fracture of the longitudinal stiffener in loading side, where the crack propagated to both sides. The failure model of the cabin is local buckling of skin due to the fracture of the longitudinal stiffener.