Rocket nozzle with reduced output section.

摘要

In a rocket motor nozzle with a selectively reduced outlet cross-sectional area, comprising a convergent part (12) receiving the gases produced in a combustion chamber (13), a nozzle throat (11) of reduced cross-sectional area (So) and a divergent cone (14) connected to the nozzle throat (11) and ending at its downstream part (15) in a gas outlet cross-sectional area (Se) defining a high cross-sectional area ratio ( epsilon = Se/So), a jettisonable annular obstacle (20) is attached to the downstream end (15) of the cone (14) so as to define, at the outlet of the cone (14) a zone (25) of selectively reduced cross-sectional area (S1) in order, in a first phase of flight, to ensure stability of the separation of the flow of hot gases relative to the wall of the cone (14).