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  • 1
    Electronic Resource
    Electronic Resource
    Combustion Wave Structure of AP Composite Propellants (1987)
    Weinheim : Wiley-Blackwell
    Propellants, Explosives, Pyrotechnics 12 (1987), S. 137-140 
    Details
    ISSN: 0721-3115
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The combustion mechanism of ammonium perchlorate (AP) composite propellants were studied. The oxidizer-rich propellants tested were made with excess concentrations of AP particles. The pressure deflagration limit of propellant decreases with increasing the concentration of binder. The combustion wave consists of two reaction regions I and II: the region I is the zone of AP monopropellant flame and the region II is the zone of diffusion flame. The heat flux feedback from the gas phase to the burning surface increases as pressure increases, and the heat flux is responsible for the burning rate characteristics.
    Additional Material: 9 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/prep.19870120407
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  • 2
    Electronic Resource
    Electronic Resource
    Energetic Solid Fuels for Ducted Rockets (II) (1991)
    Weinheim : Wiley-Blackwell
    Propellants, Explosives, Pyrotechnics 16 (1991), S. 287-292 
    Details
    ISSN: 0721-3115
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The combustion characteristics of variable-flow ducted rockets were evaluated in order to obtain optimum design parameters of the gas generators. The energetic solid fuels used for the gas generators were glycidyl azide polymer (GAP) with burning rate catalysts. The burning rate of GAP based energetic fuels was much higher than that of composite and double-base based fuel-rich propellants. The pressure exponent of the burning rate was high enough to obtain a wide range of variable-flow rat. Two types of combustion test were conducted: a semi-free jet and a direct connect flow. The pressure-time response in the primary combustor obtained by the use of a throttable nozzle was evaluated.
    Additional Material: 11 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/prep.19910160606
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  • 3
    Electronic Resource
    Electronic Resource
    Energetic Solid Fuels for Ducted Rockets (III) (1992)
    Weinheim : Wiley-Blackwell
    Propellants, Explosives, Pyrotechnics 17 (1992), S. 303-306 
    Details
    ISSN: 0721-3115
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Ducted rockets operate with the combustion of fuel-rich gas generated in a primary combustor and the ram-air induced from the atmosphere to a secondary combustor. Thus, the combustion performance depends on the mixing and reaction processes of the fuel-rich gas and the air flow in the secondary combustor. The energetic solid fuels examined in this study consisted of ammonium perchlorate based composite propellants containing boron particles. The combustion efficiency of boron particles in the secondary combustor was determined as a function of air-mixing process and air/fuel ratio. Two types of air-inlet were used to evaluate the combustion of boron particles. Combustion tests conducted by direct connect flow indicate that the combustion efficiency increased significantly when a multi-port consisting of two forward-ports and two rear-ports was used.
    Additional Material: 10 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/prep.19920170609
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