FIELD: manufacturing technology.
SUBSTANCE: invention relates to a method of producing structural laminar composite materials based on glass fabric or carbon fiber prepregs impregnated with a curable polymer and can be used in making fuselages in aircraft and aerospace engineering, as well as other purpose composite products, to strength and protective properties of which high requirements are met. Proposed method comprises metal coating of prepreg containing glass fabric or carbon fiber and polymer curable binder by plasma spraying of aluminum powder directly onto prepreg in two steps. First step is carried out at current intensity of plasmatron arc 120–140 A with introduction of disparate aluminum particles into binder, then current is increased to 150–180 A and solid metal layer is formed. Then prepreg layers are laid using metallized prepreg as outer layer and composite material is molded at temperature of 150 °C and pressure of 0.6–0.8 MPa with hardening of binder. Additional treatment of metal-coated surface of composite material is carried out by plasma-electrolytic oxidation in galvanostatic mode in conditions of anode or anode-cathode polarization of article at current density of 0.08–0.15 A/cm2 in electrolyte, containing Na3PO2⋅12H2O, Na2B4O7⋅10H2O and Na2WO4⋅2H2O at the following components content, g/l: Na3PO4⋅12H2O (20–30); Na2B4O7⋅10H2O (10–15); Na2WO4⋅2H2O (2–3).
EFFECT: improving the quality of the obtained composite materials, improving their protective, including anticorrosive properties, and fire-resistance, while simplifying the technology and reducing the time required to mold composite articles.
3 cl, 7 dwg, 1 tbl, 3 ex
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Authors
Dates
2019-09-03—Published
2018-08-17—Filed