Accession Number : AD0428602


Title :   SOLID PROPELLANT IGNITION STUDIES: IGNITION OF THE REACTION FIELD ADJACENT TO THE SURFACE OF A SOLID PROPELLANT


Descriptive Note : Final technical rept., 1 Oct 1962-30 Sep 1963


Corporate Author : PRINCETON UNIV NJ


Personal Author(s) : Hermance, Clarke E ; Shinnar, Reuel


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/428602.pdf


Report Date : 01 Dec 1963


Pagination or Media Count : 252


Abstract : The object of this research was to elucidate igni tion mechanisms of solid propellants, to identify the component processes, and to lay the basis for a theory of ignition. Experiments were performed in which composite propellant samples and polymeric fuel samples were exposed to high and low speed flows of oxygen containing gases at high temperature and pressure in a shock tunnel. Ignition of either propellant or fuel could not be obtained in high speed flows even in pure oxygen; in addition, no charring or decomposition of the fuel was observed. At low flow speeds, on the other hand, ignition of the composite propellant and the polymeric fuel did occur, and the ignition delay was found to depend on the gas phase oxygen concentration. The non-ignition at high flow speeds indicated that dilution or sweeping away of the gaseous reaction zone inhibited the ignition. Results strongly suggest that the site of ignition is in a gaseous reaction boundary layer adjacent to the surface of the propellant and not on the fuel surface itself.


Descriptors :   *SOLID PROPELLANT ROCKET ENGINES , BOUNDARY LAYER , COMPUTER PROGRAMMING , FLAMES , GASEOUS ROCKET PROPELLANTS , IGNITION , INTEGRAL EQUATIONS , LIQUID ROCKET FUELS , ROCKET ENGINES , ROCKET NOZZLES , SHOCK TUBES , SUBSONIC FLOW , SUPERSONIC FLOW , SUPERSONIC NOZZLES , SURFACES


Subject Categories : Ammunition and Explosives
      Solid Rocket Propellants


Distribution Statement : APPROVED FOR PUBLIC RELEASE