Patent ID: 6289669
Filing Date: 2001-09-18
Classification: F02K,F42B

Abstract:
A lateral thrust control apparatus for a missile comprising:a plurality of lateral thrust nozzles on the missile for communicating with a gas generator to produce a lateral thrust on the missile,a valve for each nozzle so that the nozzle is opened and closed, anda common actuator to operate each valve between open and closed positions for the respective nozzle to control flow of gases from said gas generator to said nozzles,said actuator being supported for reciprocal travel along an axis and for rotation movement around said axis, and being configured to open a selected individual nozzle while the other nozzles are closed based on a particular respective position of the actuator along and around said axis,wherein said actuator has a conical outer peripheral surface and is provided with a longitudinal control groove in said peripheral surface parallel to said axis, andwherein each said valve for each nozzle comprises a valve seat at said nozzle, a valve member for opening and closing said seat, a spring acting to open said valve, a rod connected to said valve member, a roller on said rod engaged with the peripheral surface of the actuator such that in an initial position of the actuator, the valves are all open and no net lateral thrust is produced on the missile and in an active position of the actuator, the actuator is axially and rotationally positioned so that the roller of a valve associated with a selected one of said nozzles is engaged in said groove so that said nozzle remains open while the rollers of the other of said nozzles are engaged with the peripheral surface of the actuator to close the respective valves.