公开(公告)号：JPS58121969A

公开(公告)日：1983-07-20

申请号：JP444682

申请日：1982-01-14

Applicant: NAT AEROSPACE LAB

Inventor： MITANI TOORU

IPC: A62D1/08 ,  A62C3/06

公开(公告)号：JPS60111049A

公开(公告)日：1985-06-17

申请号：JP21911183

申请日：1983-11-21

Applicant: NAT AEROSPACE LAB

Inventor： MITANI TOORU ,  NIIOKA TAKASHI

IPC: F02K9/26 ,  F02K9/00 ,  F02K9/32 ,  F02K9/38

Abstract: PURPOSE:To control a secondary flame in an efficient manner, by emitting and mixing a combustion inhibitor in and around a nozzle skirt outlet end where exhaust gas of a rocket and the atmosphere are contacted with each other, while leading the combustion inhibitor into the peripheral part of an exhaust gas stream. CONSTITUTION:A gaseous combustion inhibitor is stored in a tank 3 and emitted to a peripheral part of an exhaust gas stream 6 being high in temperature and including unburnt fuel from a combustion controlling nozzle 5 being annularly installed in and around an outlet end 2 of a nozzle skirt 1 by way of a control valve 4. Here, at a region 9 where the gas stream 6 and an air stream 8 are mixed, usually an oxidizing exothermic reaction occurs most actively and a secondary flame is made up there. And, this region is one where thickness of the combustion flame is efficiently controlled and finally extingushed. Thus, since the combustion inhibitor is not added to a solid propellant, problems on a drop in combustion capacity or physical properties and manufacturing the propellant all can be solved.