|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/322 ; 137/809 ; 137/819|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 22 인용 특허 : 1|
A fluidic thruster control system and method for guided missiles and the like, which utilizes a fluidic jet interaction device for controlling a downstream fluidic vortex amplifier to modulate exhaust flow through thrust nozzles.
A fluidic system for porportionally controlling warm gas flow through a pair of thrust nozzles, comprising: passage means for delivering gas flow from a source to said first and second thrust nozzles in parallel flow arrangement; a pair of fluidic vortex valves each having control ports for receiving proportional fluid signals and being operable to proportionally vary the rates of flow of warm gas through each of said thrust nozzles in relation to said fluid signals whereby the total flow through both of said nozzles remains substantially constant; a flo...