公开(公告)号：JPS61244861A

公开(公告)日：1986-10-31

申请号：JP8537385

申请日：1985-04-23

Applicant: NAT AEROSPACE LAB ,  NISSAN MOTOR

Inventor： NIIOKA TAKASHI ,  MITANI TORU ,  TAKAHASHI MAMORU ,  IZUMIKAWA MUNEO ,  KOREKI TAKEMASA

IPC: F02K9/95

Abstract: PURPOSE:To decrease the size and the weight of an ignitor, by a method wherein, in an ignitor which is placed in an inner hole for rocket thrust chemical, the axis of a hole bored in the ignitor is directed obliquely to the inner surface of the inner hole. CONSTITUTION:In an ignitor 20 which is disposed in an inner hole for rocket thrust chemical, a plug 21, an ignitor 22, an outer cylinder 23, and charged ignition chemical 24. A number of nozzles 25 are formed in the side wall of an outer cylinder 23. An axis of X-X of a nozzle hole 25 is inclined at an inclination angle theta with an axis O-O of an ignitor 20 so as to direct obliquely backward at an inclination angle theta with the inner surface 6 of an inner hole for thrust chemical. When charged ignition chemical 24 is ignited, after its flame is injected in the direction of the axis X-X of the nozzle hole, it is inverted to a direction Y-Y by means of an inner surface 6 of the inner hole. This causes the occurrence of turbulence in an inner hole 5, and enables reduction of the size and the weight of the ignitor.

公开(公告)号：JPH01249684A

公开(公告)日：1989-10-04

申请号：JP7616088

申请日：1988-03-31

Applicant: NAT AEROSPACE LAB ,  NISSAN MOTOR

Inventor： NIIOKA TAKASHI ,  MITANI TORU ,  MARUIZUMI HARUKI

IPC: F02K9/10 ,  C06D5/00

Abstract: PURPOSE:To increase combustion temp. and to improve secondary combustion efficiency by binding two components; metal fuel and oxidizing agent, with a binder thereby producing the propellant consisting of prescribed ratios of the metal fuel, the oxidizing agent and the binder. CONSTITUTION:The solid propellant 1 is produced by forming pellets 4 of the metal fuel, for example, particulate boron 2 and the particular oxidizing agent, for example, ammonium peroxide 3 and binding these pellets with the binder, for example, terminal carboxyl group polybutadiene 5. The content of the boron 2 in the total weight is confined to 20-40wt.% in this case. Since the solid propellant 1 consists of the metal fuel 2 and the oxidizing agent 3 which are in direct contact with each other, the propellant allows easy combustion and generates a high temp. The binder is decomposed by this high temp. to generate the gaseous hydrocarbon of high temp. Further, the gaseous hydrocarbon of high temp. is easily secondarily burned by air by which the extremely high secondary combustion efficiency is obtd.

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.