LIQUID-PROPELLANT ROCKET ENGINE CHAMBER LOCK Russian patent published in 2014 - IPC F16B2/20 

FIELD: engines and pumps.

SUBSTANCE: proposed lock comprises adjusting pyrotechnic retainer and adjustable link arranged between the chamber and engine frame. Lug is secured at combustion chamber cylindrical part while plate with pads is fitted between rods and frame base. Holes are made at said lug and pads for adjusting retainer and pyrotechnic retainer to be fitted therein. Bracket and cramp with links with holes are welded to combustion chamber cylindrical part and frame, adjusting drawbar secured by pins in links holes being arranged there between. Adjusting retainer secured at frame plate pad has one conical surface in contact with mating conical surface in pad hole and another conical guide surface at the retainer opposite side.

EFFECT: integrity of engine chambers at transportation, higher reliability of locking at engine ground tests, chamber unlocking at carrier rocket flight initial path.

5 cl, 15 dwg