| 摘要 |
FIELD: spacecraft manufacture. SUBSTANCE: primary structure 12 of spacecraft 10 has cellular core made from flexible aluminum sheet. Form of said core corresponds to form of spacecraft envelope. First and second continuous composite layers are applied on inner and outer surface of spacecraft envelope. These layers are made from prepreg layers and include fibers in polymer matrix. Core is provided with local bulges in its walls or possesses higher density at definite sections. Proposed method includes making the mandrel according to form and sizes of inner wall of primary structure of spacecraft 10. First of said prepreg sheets is applied on outer contour of mandrel. One or more prepreg sheets is applied on outer surface of core. Hardening of prepreg sheets is effected in autoclave, after which mandrel is withdrawn. EFFECT: facilitated procedure; enhanced heat conductivity; enhanced weight efficiency. 16 cl, 7 dwg |
