LIQUID PROPELLANT ROCKET ENGINE UNIT Russian patent published in 2015 - IPC F02K9/42 

FIELD: engines and pumps.

SUBSTANCE: claimed unit comprises oxidiser and propellant tanks, several modular liquid-propellant engines, common load-bearing frame and steering hydraulic drives. Note here that every modular engine comprises combustion chamber and nozzle, turbo pump unit composed by turbine, propellant and oxidiser pumps, gas generator, ACS units, pipes to feed propellant and oxidiser to gas generator and combustion chamber and gumball suspensions wit steering hydraulic drives to vary the rocket position in space. Said modular engines are composed of liquid-propellant rocket engines configured to afterburning of producer gas. Note here that engine chamber is secured at gimbal suspension relative to load-bearing frame. Said suspension incorporates bellow assembly connected via gas duct with turbine outlet and with combustion chamber head on opposite side. Note here that said load-bearing framer is composed of all-welded trussed structure. The latter is composed of the four identical sections composed of load-bearing rods and square section with bearing sites secured at section angles. Said load-bearing frame is connected with rocket frame ring by said four rods. Their ends are secured at bearing site on one side and, on opposite side, their ends, thrust bearings, are secured to rocket frame ring. Note here that said bearing rods are uniformly arranged in frame ring. Note also that joint between load-bearing frame and engine is composed of backup cylinders arranged between load-bearing sites and backup cylinder support rings. Note also that axis of backup cylinders is aligned with that of the chambers of engines.

EFFECT: higher stiffness and strength.

7 cl, 5 dwg