Stress from the ignition of a rocket is transferred from the rocket nozzle to the actuators and flexible joint seal which move the nozzle causing potential failure of the actuators. This stress can be relieved by using a snubber in the form of a flexible hollow conical toroidal bladder filled with incompressible fluid fitted snugly between the nozzle and the main body of the rocket. Such a snubber transfers the stress to the main body of the rocket through the snubber while deforming to allow the rocket nozzle to slew in response to control commands.
申请公布号
US5060550(A)
申请公布日期
1991.10.29
申请号
US19910658163
申请日期
1991.02.19
申请人
THE UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE NAVY
发明人
HOEVER, JEFFREY P.;REGINATO, RICHARD L.;BAY, FREDERIC M.;ROLON, CLAUDIA E.;BAZIGOS, MICHAEL;ALLEN, ROLLA W.