THRUST VECTOR CONTROL SYSTEM FOR A PLUG NOZZLE ROCKET ENGINE
摘要
A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug disposed within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat, and a thrust diverter moveably disposed relative to the housing to define an asymmetric pressure distribution along the plug for thrust-vectoring. In one embodiment, the thrust diverter is normally biased to a non-thrust-vectoring position, but is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.
申请公布号
WO2006028516(B1)
申请公布日期
2006.11.09
申请号
WO2005US11979
申请日期
2005.04.07
申请人
AEROJET-GENERAL CORPORATION;SOTA, CHARLES, G.;CALLIS, GEORGE, J.;MASSE, ROBERT, K.
发明人
SOTA, CHARLES, G.;CALLIS, GEORGE, J.;MASSE, ROBERT, K.