| 摘要 |
A propulsion unit nozzle for rockets, missiles and similar spacecraft, comprising a nozzle body (10) having a convergent section, throat and inlet to divergent section, and a folding divergent section, the divergent section being formed by a succession of rigid rings (23, 25) which are connected to each other and to the body of the nozzle by flexible rings (22, 24), these alternate flexible and rigid rings, which are coaxial with the axis (38) of the nozzle, being juxtapositioned one around the other and around the nozzle body to form a concertina- type profile when the divergent section is in its folded state, and being able to line up one behind the other to form the desired profile for the divergent section in the operative state under the action of unfolding control means (17) which causes the rigid rings to carry out a translation movement axially of the nozzle and towards the rear thereof, while the flexible rings turn inside out by folding back on themselves, the rigid and flexible rings thus being displaced until they take up their final positions in which they form as a whole the unfolded divergent section. <IMAGE>
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