Aircraft leading edge flap material and preparation method thereof

Abstract

The invention discloses an aircraft leading edge flap material and a preparation method thereof, which comprises the following components in parts by mass: 22-30 parts of acrylic aluminum, 30-36 parts of naphthenic chromium, 33-37 parts of manganese disulfide, and quartz silicon 25-35 parts, 27-31 parts of ferrous oxide, 35-40 parts of ethylene magnesium, 13-19 parts of olefin wax, 16-20 parts of cyclopropene copper, a leading edge flap material of an aircraft in the present invention, which can strengthen parts Hardness, reduced weight, simple and reasonable process, high production efficiency.

Description

technical field [0001] The invention relates to an aircraft leading edge flap, in particular to an aircraft leading edge flap material and a preparation method thereof. Background technique [0002] Leading edge flaps are flaps located on the leading edge of the wing, which are widely used on supersonic aircraft. Because supersonic aircraft generally use thin wings with sharp leading edges and relatively small thickness. When flying at high angles of attack, airflow separation will begin to occur on the leading edge of the upper surface of the wing, and the maximum lift coefficient will be greatly reduced. Leading edge flaps, on the one hand, can reduce the angle between the leading edge and the relative airflow, so that the airflow can flow smoothly along the upper airfoil, and on the other hand, it also increases the camber of the wing section. At present, there is no mechanical performance and mechanical properties. Aircraft leading-edge flaps with excellent performance,...

AI Technical Summary

Problems solved by technology

Because supersonic aircraft generally use thin wings with sharp leading edges and relatively small thickness. When flying at high angles of attack, airflow separation will begin to occur on the leading edge of the upper surface of the wing, and the maximum lift coefficient will be greatly reduced. Leading edge flaps, on the one hand, can reduce the angle between the leading edge and the relative airflow, so that the airflow can flow smoothly along the upper airfoil, and on the other hand, it also increases the camber of the wing section. At present, there is no mechanical performance and mechanical properties. Aircraft leading edge flaps with excellent performance, so the development of an aircraft leading edge flap material with excellent mechanical and mechanical properties has become an urgent problem to be solved