公开(公告)号：KR1020110076419A

公开(公告)日：2011-07-06

申请号：KR1020090133121

申请日：2009-12-29

Applicant: 국방과학연구소

Inventor： 고덕곤 ,  김상재

IPC: F42B15/00 ,  F02K9/97 ,  F42B10/30 ,  F41F3/04

CPC classification number: F02K9/97 ,  F41F3/04

Abstract: PURPOSE: A nozzle device for rocket for reducing tip-off and a rocket launching method are provided to prevent the tip off phenomenon by slanting combustion gas from a launching time through a deflector for a specific duration. CONSTITUTION: A nozzle device for rocket for reducing tip-off comprises a nozzle body and a deflector(142). The nozzle body is arranged in one end of a rocket main body(110) and is connected to a combustion chamber(130). The nozzle body is formed with the central axis of the main body in parallel with a center axis. The deflector makes combustion gas lean toward the central axis in the launching of the main body. The deflector ejects burning gas after the launching of the main body to the direction in parallel with the central axis. The deflector is included of an ablation material which is worn away with the combustion gas.

Abstract translation: 目的：提供一种用于减少脱落的火箭喷嘴装置和一种火箭发射方法，以通过将燃烧气体从发射时间通过偏转器倾斜一段特定持续时间来防止倾倒现象。 构成：用于减少倾倒的用于火箭的喷嘴装置包括喷嘴体和偏转器（142）。 喷嘴主体配置在火箭主体（110）的一端，与燃烧室（130）连接。 喷嘴体与主体的中心轴线平行于中心轴线形成。 导流板在主体的发射中使燃烧气体朝向中心轴线倾斜。 导向器在主体发射到与中心轴线平行的方向后喷射燃烧气体。 包括与燃烧气体一起磨损的消融材料的偏转器。