| 摘要 |
#CMT# #/CMT# The device has a flow device (2) that is positioned around the nozzle (1). The flow device is separated from a rocket engine. The flow device is provided for generating a gas flow (3) with a component (R) in a direction of a gas-discharging channel (A) of the nozzle during switching on and off of the rocket engine. The gas flow surrounds a periphery of a gas outlet (1a). #CMT# : #/CMT# An independent claim is also included for a method for reducing a force effect of a nozzle of a rocket engine. #CMT#USE : #/CMT# Device for reducing a force effect of a nozzle of a rocket engine. #CMT#ADVANTAGE : #/CMT# The flow device is positioned around the nozzle, and is separated from a rocket engine for generating a gas flow with a component in a direction of a gas-discharging channel of the nozzle during switching on and off of the rocket engine, and thus enables to reduce a force effect of the nozzle without structural changes of the rocket engine. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a side view of a nozzle of a rocket engine. 1 : Nozzle 1a : Gas outlet 2 : Flow device 3 : Gas flow A : Gas discharging channel R : Component. |
