FIELD: rocketry; space engineering.
SUBSTANCE: two-stage carrier rocket return upper stage under detachable payload adapter comprises rotor assembly, which provides controlled movement along trajectory of descent from orbit "as per helicopter" in mode of autorotation and bringing of stage to specified area of landing. Rotor blades are laid along the stage body before launching. On stage tail compartment before launching carrier rocket there are four rotary flaps of tail fairing, equipped with longitudinal and transverse power set and controlled pneumatic rod and laid before launching carrier rocket outside along the body of its lower stage. After output of braking pulse of de-orbit, rotor blades are released and their output into working position due to incoming air flow, connection of tail fairing flaps to form a single tail fairing structure and transfer of rotor to autorotation mode and oriented position of stage relative to direction of incoming air flow.
EFFECT: reliable drive of the stage to the specified area.
7 cl, 2 dwg
