Patent ID: 7568348

Claim:
A nozzle assembly for thrust or thrust vector control of a rocket or ramjet, comprising: an elongated nozzle housing having a forward end portion and a rear end portion spaced longitudinally from said forward end portion; a pair of vane members mounted on said nozzle housing for pivotal movement within the central portion of said nozzle housing, said vane members extending vertically or transversely between the upper and lower portions of said nozzle housing near said forward end portion thereof, said vane members extending longitudinally in said nozzle housing from said forward end portion thereof to a point near said rear end portion thereof; said vane members being pivotable about axes disposed between the forward and rear ends thereof, and being movable between an open position wherein they are in substantially parallel relation so that gases can flow between them and also between said vane members and said nozzle housing, and a closed position wherein their forward ends are in engagement with each other and their rear ends are in engagement with the adjacent inner surface of said nozzle housing; and an operating mechanism operatively connected to said vane members to move them simultaneously or individually between said open and closed positions for thrust control or thrust vector control.