FIELD: space engineering.
SUBSTANCE: proposed space launch vehicle includes boost stage connected in succession by means of connecting bays and provided with solid-propellant engine plants with nozzle units. Launch vehicle is also provided with development engine, gas-jet orientation system, tail fairing and nose fairing equipped with solid-propellant separation and withdrawal engine. Provision is made for plane of transversal separation with one of stages of launch vehicle. Mounted on this plane are attachment and separation units for nose fairing. Front part of sectional envelope has end face closed at top; it is used for placing the payload and adapter for its attachment. Located between front part of envelope and its rear part which is open at end faces is additional transversal separation plane with separable attachment units. Space launch vehicle is provided with apogee stage located under nose fairing and fitted with autonomous nose module which is formed by front part of nose fairing, adapter and payload. Apogee stage has instrument bay, solid-propellant engine plant and tail compartment. Autonomous nose module of apogee stage is fastened with instrument bay by means of said separable attachment units. Located between apogee stage and next-to-last boost stage is elongated cylindrical compartment which is connected with transversal separation plane of nose fairing. Engine plant of final boost stage is located inside elongated cylindrical compartment. Mass of payload is increased due to location of apogee stage under fairing and final boost stage under connecting compartment.
EFFECT: extended field of application of multi-stage space launch vehicle.
8 cl, 4 dwg
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