TY - GEN
T1 - Combustion characteristics of the cylindrical multi-port grain for hybrid rocket motor
AU - Kim, Soojong
AU - Lee, Jungpyo
AU - Kim, Gihun
AU - Cho, Jungtae
AU - Moon, Heejang
AU - Sung, Honggye
AU - Kim, Jinkon
AU - Park, Suhyang
PY - 2009
Y1 - 2009
N2 - The purpose of this experimental research is to investigate combustion characteristics of cylindrical multi-port grain of a hybrid rocket motor. The physical model of concern includes an oxidizer supply system, a multi-port fuel grain, and a combustor with pre- and post chamber. Gaseous oxygen and polymer (PE and PMMA) are applied as the oxidizer and the fuel, respectively. In geometric points of view, the effects of the port number and the distance between ports on a regression rate are taken into account. Internal combustion performance was analyzed using small- and large scale motors: one is motor diameter of 50 mm and the other is 96 mm, with oxidizer mass flux ranging from 10 kg/m2-sec to 300 kg/m2-sec for both cases. The port number positively shifts the O/F ratio to near its optimum value as well as the oxidizer mass flux to the typical range influenced by pressure effects so that the fuel regression rate becomes fast as the port number increases to a typical number up to 4 ports. Emphasis was placed on merging effects among fuel gain ports having 4 and 5 port to analyze how port geometrical configuration may influence the chamber pressure and thrust drop.
AB - The purpose of this experimental research is to investigate combustion characteristics of cylindrical multi-port grain of a hybrid rocket motor. The physical model of concern includes an oxidizer supply system, a multi-port fuel grain, and a combustor with pre- and post chamber. Gaseous oxygen and polymer (PE and PMMA) are applied as the oxidizer and the fuel, respectively. In geometric points of view, the effects of the port number and the distance between ports on a regression rate are taken into account. Internal combustion performance was analyzed using small- and large scale motors: one is motor diameter of 50 mm and the other is 96 mm, with oxidizer mass flux ranging from 10 kg/m2-sec to 300 kg/m2-sec for both cases. The port number positively shifts the O/F ratio to near its optimum value as well as the oxidizer mass flux to the typical range influenced by pressure effects so that the fuel regression rate becomes fast as the port number increases to a typical number up to 4 ports. Emphasis was placed on merging effects among fuel gain ports having 4 and 5 port to analyze how port geometrical configuration may influence the chamber pressure and thrust drop.
UR - http://www.scopus.com/inward/record.url?scp=77957853039&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:77957853039
SN - 9781563479762
T3 - 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
BT - 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
T2 - 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Y2 - 2 August 2009 through 5 August 2009
ER -