국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Development Test of a Liquid Apogee Engine for the ETS-VI
저자	Roket Propulsion Research Division
Keyword	Bipropellant apogee engine; ETS-VI; Blowdown system
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01250.pdf?id=NALTR0001250
보고서번호	NAL TR-1250
발행년도	1994.10
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	the preliminary development phase of the apogee engine,a peak vacuum specific impulse Ispv of 325 s was set as the initial development target.This performance requirement of the apogee engine is greater than that of the bipropellant engine using NTO/monomethyl hydrazine (MMH).To meet such high performance requirements,we empoyed a NTO/N2H4 propellant system instead of NTO/MMH propellant and used a very large area ratio nozzle (nozzle area ratio is 200 to 300).To enhance the reliability of the apogee propulsion system,we selected a pressure-fed,full-blowdown system.Fundamental studies including hard-start,pop and thermal problems were also conducted during the development series of apogee engine started in 1983. Performance characteristics of apogee engine developed in 1990 was as follows;chamber pressure Pc=0.97～0.63 MPa,mixture ratio MR=0.85～1.05,vacuum thrust=1980～1280 N,mean vaccum specific impulse Ispv=0320.0±2.7 s,and total burn time=2900 s.Delivered peak Ispv was less than the initial development tt,however,the engine performance was higher than that of the engine for NTO/MMH propellant.This paper describes mainly the development studies of the injectors used in the apogee engine.