LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2012 - IPC F02K9/56 F02K9/80 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises combustion chamber with bearing fitted on its head and provided with moving and fixed spherical support surfaces to take up forces and to control thrust vector. Note here that radius of said spherical support surface of said bearing is selected proceeding from the condition: where: Δl is tolerable crosswise shift of engine in its deviation through angle α relative to initial position; α is required maximum angle of engine turn; γ is design angle defines as: H is engine structural height defined as distance from chamber nozzle edge plane to bearing spherical surface top point, R is bearing spherical surface radius, r is size defining arrangement of chamber critical element from its lengthwise axis.

EFFECT: reduced radial shift of engine critical elements.

3 cl, 2 dwg