Accession Number : AD0467728


Title :   SOLID PROPELLANT COMBUSTION MECHANISM STUDIES


Descriptive Note : Technical progress repts. no. 15 and 16


Corporate Author : PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES


Personal Author(s) : Cole, Richard B ; Wenograd, Joseph ; Summerfield, Martin


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/467728.pdf


Report Date : 17 Jun 1965


Pagination or Media Count : 140


Abstract : Two composite solid propellant combustion experiments aimed at further elucidation of combustion mechanism are reported; one deals with burning surface photomacroscopy, the other, with low pressure combustion and oxidizer particle size influences on it. The first investigation involved photography of the surfaces of 1/4 inch square polysulfide-ammonium perchlorate (unmetallized) propellant strands during combustion in a coaxially-flowing nitrogen environment. Intense electronic flash illumination was used to render the luminosity of the flame photographically negligible, and the externallylighted surface was thereby viewed obliquely through the propellant flame zone at up to seven times magnification. The second investigation dealt with the dependence of the sub-atmospheric pressure burning rates of 1/4 inch square strands of ammonium perchlorate (polybutadieneacrylic acid and polysulfide, unmetallized) propellants on pressure and oxidizer particle size.


Descriptors :   *SOLID ROCKET PROPELLANTS , OPTICAL EQUIPMENT , PARTICLE SIZE , POLYMERS , COMPOSITE MATERIALS , THEORY , ACRYLIC RESINS , COMBUSTION , FEASIBILITY STUDIES , PRESSURE , AMMONIUM COMPOUNDS , IGNITION , FLAMES , BURNING RATE , SULFIDES , PERCHLORATES , BUTYL RUBBER , ELECTRONIC PHOTOFLASH EQUIPMENT , SOLID ROCKET OXIDIZERS


Subject Categories : Solid Rocket Propellants


Distribution Statement : APPROVED FOR PUBLIC RELEASE