국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Experimental of Rocket-Ram Combined Combustor
저자	Kazuo SATO, Hiroshi SAKAMOTO, Masaki SASAKI, Fumiei ONO, Nobuyuki YATSUYANAGI
Keyword	Combined engine; Propulsion; Liquid rocket
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01249.pdf?id=NALTR0001249
보고서번호	NAL TR-1249
발행년도	1994.10
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	be expected to increase the specific impulse significantly in parallel operation.In this paper,the superiority in the specific impulse of the double-nozzle type of rocket-ram combined engine over the single-nozzle type combined engine was shown by performance calculations.Then,a double-nozzle type of rocket-ram combined combustor with a total thrust of 5kN was designed and experimentally tested with varying ratios of thrust produced by rocket and ramjet.The propellants are LOX/kerosene＋hydrogen for rocket combustion and air-hydrogen for ram combustion.With the thrust chamber having different diverging half-angles,namely 10°18’,and 6°40’,thrust and pressure distribution along the common expansion nozzle were measured to investigate the effect of interaction of the expanding gases of rocket and ram on thrust.Enhancement of the specific impulse was experimentally verified.That is,the specific impuse which was gained in rocket-ram parallel operations,when the thrust ratio of rocket to ram was 50 to 50,was foo increase 90 percent over those in pure rocket operations.