Rocket engine with thrust direction modifying devices

摘要: 1. A rocket engine comprising, in combination, a manifold for introducing propellants into combustion chamber, wall having hemispherical deflecting surface fixed to an intermediate portion of said and extending aft therearound, conical chamber communicating with the end its larger open positioned adjacent but spaced from define expansion exhaust nozzle throat therewith, apertures formed apex bleeding gases therethrough, means vary thrust vector operation.