Method for preparing low-absorptivity high-hemispherical-emissivity oxidation film on surface of aluminum through electro-deposition

Abstract

The invention relates to a method for preparing a thermal control coating on the surface of aluminum alloy through ultrasonic pulse electro-deposition, in particular to a preparation method of preparing a composite oxidation film with the low solar absorptivity / hemispherical emissivity ratio on the surface of aluminum alloy. The preparation method comprises the following steps that 1, pretreatment is conducted on the surface of the aluminum alloy; 2, anodizing is conducted on the aluminum alloy; and 3, the oxidized aluminum alloy is subjected to ultrasonic pulse electro-deposition to prepare silicon dioxide sol, then, the surface of the aluminum alloy is cleaned with distilled water and dried, and a low-absorptivity high-emissivity thermal control coating on the surface of the aluminum alloy is obtained. The solar absorptivity of the coating is 0.10-0.20, the hemispherical emissivity of the coating is 0.80-0.95, and the thermal control coating which is low in solar absorptivity and high in hemispherical emissivity has good performance.

Description

technical field

[0001] The invention relates to a method for preparing an oxide film with low absorptivity and high hemispherical emissivity by electrodeposition on the surface of aluminum, in particular to a pulse ultrasonic electrodeposition preparation method for preparing a low-ratio solar absorptivity / hemispherical emissivity composite oxide film on the surface of an aluminum alloy , including anodic oxidation of aluminum alloy and in-hole pulse ultrasonic electrodeposition. Background technique

[0002] With the development of space vehicle technology, temperature control has become more and more important. Spacecraft experience extreme temperature cycles in orbit due to direct sunlight on one side and extremely cold space on the other. This would make the surface temperature of the spacecraft very variable, ranging from -200°C to +200°C, and in the absence of an atmosphere, heat exchange between the spacecraft and the external environment would be limited to radiatio...