Accession Number : AD0476617


Title :   LARGE SOLID-PROPELLANT BOOSTERS EXPLOSIVE HAZARDS STUDY PROGRAM (PROJECT SOPHY)


Descriptive Note : Final rept.


Corporate Author : AEROJET-GENERAL CORP DOWNEY CA RESEARCH DIV


Personal Author(s) : Irwin, O R ; Roark, G L ; Salzman, P K


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/476617.pdf


Report Date : 24 Nov 1965


Pagination or Media Count : 328


Abstract : Experimental and theoretical studies aimed at evaluating the detonation characteristics of solid-composite propellant rocket motor grains are described. A combined experimental-theoretical program was conducted to determine the effect of RDX adulterant concentration on the critical diameter of a typical Class 2 (AP-PBAN type) propellant. The resulting detonation model indicated that the critical diameter of AP-PBAN type propellant is about 75 in. Experiments were conducted to test the validity of a previously developed theory of critical geometry that (1) relates the critical diameter to the minimum size of shapes other than solid right cylinders that will sustain detonation and (2) consider the effect of donor intensity, configuration, and location on initiation of detonation in an acceptor. The experimentally determined critical dimensions for detonation of the various shapes tested were in reasonable agreement with predictions of the theory. The initiation criteria proposed by the critical geometry theory was measured and found to correctly predict the initiation of detonation in a supercritical acceptor charge by an axial, end donor. Supercritical charges could be initiated to detonation by an axial, end donor whose diameter was only about 40% of the critical diameter of the acceptor.


Descriptors :   *SOLID PROPELLANT ROCKET ENGINES , *COMPOSITE PROPELLANTS , EXPERIMENTAL DATA , HAZARDS , THEORY , EXPLOSIVE CHARGES , MATHEMATICAL PREDICTION , CYLINDRICAL BODIES , RDX , ROCKET PROPELLANT GRAINS , DETONATIONS , EXPLOSIVES INITIATORS


Subject Categories : Explosions
      Solid Propellant Rocket Engines
      Solid Rocket Propellants


Distribution Statement : APPROVED FOR PUBLIC RELEASE