| 摘要 |
FIELD: aerospace engineering. ^ SUBSTANCE: proposed flange point joint can be used to preserve or minimise deformations of space vehicle power units outer surfaces subjected to notable temperature differences in operation, or to irregular loading by outer and inner pressures. The proposed joint comprises two frames linked, on one side, with structural elements of docking compartments, and, on the other side, in contact, by its flanges, with the joint surface. It features local bulges at joint points for threaded holes receiving pints on one of the frames. The second frame, furnished with packing and protective cover, features cutouts to receive fastening nuts. The wall representing plates to deform radially in radial displacement of structural elements relative to each other is arranged on the second frame between the frame proper and the flange in contact with the first frame. Aforesaid wall acts as deformable compensator. Plate cutouts allow access to flange joint elements. ^ EFFECT: reduced weight, higher reliability of joint under cyclic loads of temperature and pressure. ^ 3 cl, 7 dwg |
