Fuselage material: lightweight and high strength
The high altitude, high speed, and high maneuverability of fighter require that the structural material selection of the fighter must meet the requirements of sufficient strength and stiffness. According to the requirements analysis of structural material selection and manufacturing process of advanced fighter (Li Hanghang, et al., International Symposium on high energy beam processing technology, October 2004). In the late 1990s, the fourth generation fighter represented by the U.S. F-22 fighter appeared. The aircraft structure adopts a wing-body fusion structure, rhombic wing, cambered double vertical tail, and large edge strip wing. Although the aircraft structural materials are still mainly metal materials, the consumption ratio of traditional steel and aluminum alloy materials is higher The number of cases has decreased to less than 20%. The amount of titanium alloy and composite materials greatly exceed this proportion. The main reasons for such material selection of F-22 aircraft are: first, to reduce the structural weight; The second is to meet the structural strength requirements under high-temperature conditions; Third, the stealth requirements of the aircraft structure are realized, and the structural weight coefficient of the aircraft is reduced to 27.8%.
