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: 0.142 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.v4.i1-6.660
pages 706-718

POLYNIMMO, A CANDIDATE BINDER FOR SOLID FUEL GAS GENERATOR PROPELLANTS

P. J. Honey
WX4 Department, Defence Research Agency, Fort Halstead, Sevenoaks, Kent, TN14 7BP, England
D. W. Anderson
WX4 Department, Defence Research Agency, Fort Halstead, Sevenoaks, Kent, TN14 7BP, England
G. A. Spinks
WX4 Department, Defence Research Agency, Fort Halstead, Sevenoaks, Kent, TN14 7BP, England
A. V. Cunliffe
WX4 Department, Defence Research Agency, Fort Halstead, Sevenoaks, Kent, TN14 7BP, England
D. A. Tod
WX4 Department, Defence Research Agency, Fort Halstead, Sevenoaks, Kent, TN14 7BP, England

要約

An investigation of polyNIMMO's potential, as both binder and oxidiser, in a high energy smokeless solid fuel gas generator propellant comprised part of a UK ramrocket development programme. The benchmark trial showed polyNIMMO's burn rate was considerably lower than GAP, or polyGLYN. The advantages and disadvantages of various binary mixtures of polyNIMMO with fuels, oxidisers, plasticisers and bum rate catalysts are discussed. The conclusions drawn from this study were applied to multiple component polyNIMMO formulations, with volumetric heat values of up to 32200 MJ/m3 (∼500 Btu/in3). Difficulties with ignitability of fuel-rich systems were observed. Comparison of the chamber temperature (which varied, significantly, with pressure) with the burn rate proved to be a more suitable method for assessment of ignitability than the formulations temperature of ignition. The relationship observed between the calculated chamber temperature and experimental burn rate will be discussed in greater detail. This work has shown that the smokeless fuel-rich polyNIMMO gas generator compositions examined possess the basic characteristics required for an air-breathing radial-burner motor configuration. Effort is currently focused on achieving a smokeless fuel-rich formulation (≈32200 MJ/m3) possessing a high pressure exponent (∼0.5-0.7) with a slow, stable, bum rate (∼0.7 mm/s) at low pressure (<3 MPa).


Articles with similar content:

PROPERTIES OF ADN PROPELLANTS
International Journal of Energetic Materials and Chemical Propulsion, Vol.5, 2002, issue 1-6
Alice I. Atwood, Alan D. Turner, P. O. Curran, May Lee Chan, Russ Reed
DEVELOPMENT OF A DIRECT INJECTION GAS-HYBRID ROCKET SYSTEM USING GLYCIDYL AZIDE POLYMER
International Journal of Energetic Materials and Chemical Propulsion, Vol.18, 2019, issue 2
S. Hatano, Yo Kawabata, Keiichi Hori, Ayana Banno, T. Oda, Hiroshi Hasegawa, Yutaka Wada
STUDIES ON CURING OF GLYCIDYL AZIDE POLYMER USING ISOCYANATE, ACRYLATE AND PROCESSING OF GAP-BORON−BASED, FUEL-RICH PROPELLANTS
International Journal of Energetic Materials and Chemical Propulsion, Vol.15, 2016, issue 3
Anu Abirami, R. V. Singh, Prashant S. Kulkarni, Mehilal, N. T. Agawane, R. R. Soman, Jagdish G. Bhujbal
BORON PROPELLANTS FOR DUCTED ROCKET APPLICATION
International Journal of Energetic Materials and Chemical Propulsion, Vol.2, 1993, issue 1-6
Christian Perut, B. Mahe
COMBUSTION OF PTFE-BORON COMPOSITIONS FOR PROPULSION APPLICATIONS
International Journal of Energetic Materials and Chemical Propulsion, Vol.11, 2012, issue 5
Grant A. Risha, Chad A. Stoltz, Vasant S. Joshi, Terrence L. Connell, Jr., Reed H. Johansson, Gregory Young, Brian P. Mason, Richard A. Yetter