FIELD: transport.
SUBSTANCE: invention relates to space engineering. Carrier rocket stage comprises central sustainer and several solid-propellant engines arranged around said central sustainer. Every solid-propellant engine features conical generatrix of solid propellant charge attached to conical capsule-type all-wound airframe made of composite material. Said conical generatrix of solid propellant engine is parallel about carrier rocket cylindrical surface generatrix. Angle of solid-propellant engine inclination to carrier rocket axis is selected to make the former pass through center of gravity of equipped carrier rocket. Every solid-propellant engine comprises hinged control nozzle turning through minor angle not exceeding inclination of solid-propellant engine axis to carrier rocket axis.
EFFECT: higher efficiency and reliability.
3 dwg
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