ROCKET FOR SPACE MISSION Russian patent published in 1994 - IPC

FIELD: space technology. SUBSTANCE: rocket for space mission is provided with three sustainer stages each composed of solid-propellant rocket engine with nozzle unit, arranged in series one after other and interconnected. Engines of first sustainer stage and of launching stage are joined with the aid of first coupling section. One butt of it is joined to first sustainer stage on side of its nozzle unit located inside its space and the other one - to engine of launching stage via intermediate member on side opposite to butt of attachment to rear section. Lattice rudders and stabilizers are mounted for turning and fixing in predetermined position on outer side surface of rear section. Outer side surface of engine of launching stage carries two jettisoned bearing bands. Other butt of engine of first sustainer stage is coupled with butt of engine of second sustainer stage via second coupling section. Nozzle unit of engine of second sustainer stage is located inside second coupling section. Other butt of engine of second sustainer stage is connected via additional member to butt of transition section. Third coupling section is attached to opposite butt of transition section. Engine of third sustainer stage is provided with gas-jet orientation system. Nozzle unit of third sustainer stage which carries gas-jet orientation system including gas generators, distributors, nozzle units and collector intercoupling them is placed inside transition section and is supported as cantilever by its butt opposite to its nozzle unit. Engine of third sustainer stage is coupled to transition section over contour internal with respect to attachment unit of transition and third coupling sections. One jettisoned bearing band is put on engines of first and second sustainer stages, coupling first and second sections are fitted with longitudinal and lateral units to divide them into parts. Last stage includes intercoupled aggregate and instrumentation sections and platform. Aggregate section and platform are also interconnected. Instrumentation section is put inside last stage and is attached to it. Aggregate section is fastened to free butt of third coupling section with the use of disintegrating attachment units. Orbital spacecraft is anchored with the help of special device on free butt of platform. It has solid-propellant controlling engine plants. EFFECT: improved operational characteristics of space mission rocket by simplification of its preparation for launch and capability to transport it to launching pad on specialized motor vehicle ready for launch. 21 cl, 8 dwg