| 摘要 |
FIELD: aircraft industry; antenna ceramic nose domes. SUBSTANCE: rocket cone has ceramic envelope joined through heat insulator with metal frame by elastic compound matched in temperature coefficient of linear expansion with envelope. Angular or sector-shaped collar is disposed on outer surface of frame in vicinity of its attachment to rocket body. Heat insulator is made of envelope material and rigidly fixed to, or built integral with, envelope. Compound is mixture of polysiloxane paste and catalyst and functions to provide for elastic linkage between parts through adhesive sublayers applied to parts being joined. Flexible ferrule is inserted in cone interior expanding toward butt end which is formed by inner surface of heat insulator and outer surface of frame. Ratio of maximal thickness of frame wall to minimal total thickness of envelope and heat insulator at frame-to- envelope joint is 0.1-0.3, maximal thickness of compound layer is greater by 1.5 to 2.0 times than maximal operating difference of axial temperature strains of parts being joined; maximal thickness of compound layer is two or three times greater than minimal value. Fastening collar made in the form of ring sectors has total peripheral length of sectors amounting to 0.2-0.45 of perimeter length. Flexible ferrule material is molded to ceramic envelope butt end; through radial slits are made in tail end of frame and additional circular metal component is inserted between fastening collar of frame and ceramic envelope butt end of cone. EFFECT: improved performance characteristics. 5 cl, 1 dwg _ |
