FIELD: aerospace aids.
SUBSTANCE: group of inventions relates to aerospace means and methods of flight using direct-current ejector thrust of said means. This thrust is created by proposed reusable ejector stage (ES) of carrier rocket (CR), including cage (1), formed by vertical rods (2) and stiffness rings (3). Steps (8) of known CR (for example, "Angara") with skewed fairings (6) and installed behind the cut of rocket engines (RD) by circular landing supports (12) are fixed to the rods, having turbulent cutouts (not shown). Starting supports (28) on ends of rods (2) serve for installation of CR ES on launching table (25). During operation of the jet engine their jet is ejected and heated (during afterburning) air through annular assembly of CR steps and through annular supports (12), activating air warming in turbulent zone. Exhausted assembly of stages of CR lands on supports (12) at launching point.
EFFECT: technical result consists in improvement of efficiency of multiple use of known stages of CR at minimum costs for their modernization.
7 cl, 6 dwg
