Accession Number:

ADA248445

Title:

Theory of Combustion of Liquid Propellants Based on Hydroxylammonium Nitrate

Descriptive Note:

Final rept.

Corporate Author:

CALIFORNIA UNIV SAN DIEGO LA JOLLA

Personal Author(s):

Report Date:

1992-01-29

Pagination or Media Count:

7.0

Abstract:

Deflagration velocities of liquid propellants based on hydroxylammonium nitrate are controlled by the chemistry of decomposition of this oxidizer in aqueous solutions. Theory was developed for the deflagration velocity and its dependence on oxidizer concentration, giving excellent agreement with experiment and suggesting that the rate of the initial proton-transfer step determines the deflagration rate. Nitramine deflagration also was considered, with two-phase flow in the reaction zone taken into account, employing empirical one-step Arrhenius chemistry. Although excellent agreement of theoretical deflagration rates with experiment was obtained from 0.5 to 103 atm, attempts to relate the one-step rate constants to rates of known elementary steps were only partially successful. Asymptotic analysis was also completed for the structure and burning velocity of carbon monoxide-nitrous oxide flames, which have some relevance to propellant deflagration. For these last flames, there is good agreement with numerical integrations, and differences from experiment are explicable. in general, the research advances our understanding of homogeneous propellant deflagration.

Subject Categories:

  • Inorganic Chemistry
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE