ライブラリ登録: Guest
Begell Digital Portal Begellデジタルライブラリー 電子書籍 ジャーナル 参考文献と会報 リサーチ集
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2015011593
pages 221-239

COMBUSTION AND PERFORMANCE STUDIES OF GLYCIDYL AZIDE POLYMER AND ITS MIXTURES AS HYBRID ROCKET FUEL

Po-Jul Chang
Graduate School of Engineering, the University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8654, Japan
Yutaka Wada
Akita University, 1-1, Tegata, Gakuen-machi, Akita City, Akita, 010-8502, Japan
Akshay Garg
Graduate School of Engineering, the University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8654, Japan
Hideo Nakayama
IHI Aerospace Co., Ltd., 1-1 Toyosu 3-chome, Koto-ku, 135-0061, Japan
Motoyasu Kimura
NOF Corporation, Yebisu Garden Place Tower, 20-3, Ebisu 4-chome, Shibuya-ku, Tokyo, 150-6019, Japan
Keiichi Hori
Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan

要約

The combustion of glycidyl azide polymer (GAP) was investigated. The GAP fuel tests were conducted in a strand burner with nitrogen gas purge and in a lab-scale hybrid rocket with gas oxygen as oxidizer. In the strand burner, at intermediate pressure range 3−6 MPa, burning rates of both cured and uncured GAP were nearly the same and strongly depend on the chamber pressure. At pressure larger than 6 MPa, uncured GAP shows less dependence on pressure, and the GAP ratio of mixtures begins to have dominant role on burning rate. Transition pressure region was observed, which was in between the pressure dependence to composition dependence. The fluctuating burning rate was the main appearance in the transition pressure region. The Zel'dovich formula shows good prediction for burning rate at intermediate pressure range, but has much deviation at high pressure due to the surface instability. A smaller sample tube can restrict the burning surface from twisting, and the resulting burning rate shows good agreement with Zel'dovich formula prediction. Uncured 100% GAP can reach its maximum burning rate at certain pressure less than 10 MPa. Based on the assumption that condensed phase reaction is the only heat source which dominates the burning rate, the prediction of maximum burning rate of GAP mixture is also possible. In a lab-scale hybrid rocket test, GAP/PEG solid fuel demonstrated a very good burning rate under mild chamber pressure and oxygen flux. Instantaneous burning rate was successfully measured by ultrasonic techniques, and the results implied complex internal ballistic behavior.


Articles with similar content:

HIGH BURNING RATE SOLID ROCKET PROPELLANTS
International Journal of Energetic Materials and Chemical Propulsion, Vol.4, 1997, issue 1-6
G. Doriath
INVESTIGATION OF SOLID OXIDIZER AND GASEOUS FUEL COMBUSTION PERFORMANCE USING AN ELEVATED PRESSURE COUNTERFLOW EXPERIMENT FOR REVERSE HYBRID ROCKET ENGINE
International Journal of Energetic Materials and Chemical Propulsion, Vol.11, 2012, issue 6
Grant A. Risha, Terrence L. Connell, Jr., Reed H. Johansson, Gregory Young, Richard A. Yetter
EFFECTS OF DIFFERENT DECELERATION AGENTS ON THE PROPERTIES OF HYDROXYL TERMINATED POLYETHER (HTPE)-BASED COMPOSITE SOLID PROPELLANTS
International Journal of Energetic Materials and Chemical Propulsion, Vol.16, 2017, issue 2
Luigi T. DeLuca, Weiqiang Pang, XueZhong Fan, Huan Li, XiaoLong Fu, Ke Wang, JunQiang Li
EFFECTS OF METHANOL AND FUMED SILICA ON LINEAR BURNING RATES OF AQUEOUS HYDROXYLAMMONIUM NITRATE
International Journal of Energetic Materials and Chemical Propulsion, Vol.14, 2015, issue 1
Kenneth W. McCown III , Eric L. Petersen
IGNITER COMPOSITIONS FOR LOVA AND DOUBLE-BASE PROPELLANTS CONTAINING KDN
International Journal of Energetic Materials and Chemical Propulsion, Vol.18, 2019, issue 2
E. Roth, Stefan Kelzenberg, Sebastian Knapp, Volker Weiser, A. Koleczko