Abstract: The polyimide fiber/epoxy (PI/EP) composite laminates were prepared by hot-melt method combined with autoclave molding technology using high strength and high modulus PI fiber as reinforcement and aviation grade EP as matrix. The mechanical properties and failure morphology of the PI/EP composites were analyzed. The results show that PI fiber exhibits good interfacial bonding strength with epoxy resin. The interlaminar shear strength of the PI/EP composites is 65.2 MPa and the in-plane shear strength is 68.6 MPa; The PI/EP composites possess excellent mechanical properties because of good interface bonding integration condition, the longitudinal tensile strength is up to 1 835 MPa and the flexural strength is 834 MPa. The longitudinal tensile failure form of the PI/EP composites is explosion damage of filament. The high strength and high modulus PI fiber has excellent toughness and high elongation, so the time of failure becomes longer when the PI/EP composites are subjected to great tensile stress. The longitudinal compression failure form is 45° kinking band. The high strength and high modulus PI/EP composites provides a new material selection scheme for advanced aerospace composites.