ROCKET Russian patent published in 2017 - IPC F42B15/00 

FIELD: mechanical engineering.

SUBSTANCE: invention is relevant to rocket engineering and can be used in small-size rockets equipped with detachable launching stage. Rocket is provided with main propulsion stage fixed in transitional structural ring with the aid of crushable members, detachable launching stage equipped with engine fastened to transitional structural ring with the aid of swivel nut, plunger and low-drag fairing. At that, swivel nut is provided with lock nut mounted with sweeping low-drag fairing. Plunger is fastened to after-body of main propulsion stage strengthened to transitional structural ring with the aid of crushable members. Transitional structural ring is provided with perforations in the form of longitudinal channels, which form accumulation chamber together with inner cavity of transitional structural ring, after-body of main propulsion stage and with engine. This chamber is opened in atmosphere with the aid of channels of air inlets. Each of these channels is made in the form of diffuser and mounted with rest on inner part of low-drag fairing provided with through slot. Slot is made with sweeping of air inlet and placed on external surface of low-drag fairing from rear edge to ring flat-bottom recess. Nut with rest on flat bottom of ring recess is mounted on each air inlet. Frontal part of each air inlet is provided with radial recess turned into flattened surface, which is placed perpendicular to longitudinal axis of rocket. Width of the said flattened surface is not less than that one of diffuser input part. Aerodynamic cone is movably mounted on after-body of main propulsion stage. It is pushed up by spacer nut from edge of transitional structural ring, which is joined with aerodynamic cone with the aid of hook-end made in the form of separate sections. These sections are uniformly placed with sweeping of main propulsion stage and kept from angle displacements with the aid of rigid overhangs.

EFFECT: invention provides simplification of rocket design and simultaneously increasing reliability of its operation.

7 dwg