This paper is based on a national key project stratospheric long-endurance fixed-wing UAV project， which studies the manufacturing technology of wing structural components for unmanned aerial vehicles. To meet the strength， stiffness and stability of the wing structure， the main beam and leading edge of the carbon fiber composite foam sandwich structure were solidified using external molding and internal pressure， combined with hot plate oven heating technology. Load test and finite element analysis were conducted on the main beam products. According to the analysis results，the surface of the main beam product was reinforced.The results indicate that the reinforced main beam product can withstand 2.5 times the rated load and bear atorque of 102N·m， and the total weight of the main beam products was 7.2kg and the leading edge products weighed 0.19kg，achieving the lightweight of the wing structural components.The developed products meet the requirements of various indicators， and provide a new technical approach for the forming of ultra-light carbon fiber composite structural parts.