TWO-STAGE LAUNCH VEHICLE Russian patent published in 1997 - IPC

FIELD: space engineering; rocketry. SUBSTANCE: two-stage launch vehicle has nose unit with Payload, first-stage rocket unit with inter-unit adapter compartment provided with separation unit and second-stage rocket unit which consists of two half-units mounted in parallel. Half-units have different length; they are engageable by their lateral sides. Oxidizer half-unit contains cryogenic oxidizer tank and fuel half-unit contains cryogenic fuel tank, liquid-propellant rocket engine and oxidizer supply pipe line for feeding the engine. Oxidizer half-unit is connected with front part of fuel half-unit by means of load-bearing tie units; fuel half-unit has larger length; it is connected to oxidizer supply pipe line. First-stage rocket unit is located after second- stage oxidizer half-unit coaxially with it and is connected with this unit by means of inter-unit adapter compartment, thus making it possible to mount first- and second-stage engines in parallel. EFFECT: enhanced reliability. 5 cl, 4 dwg