Accession Number:

ADA019674

Title:

Steady-State Combustion of Nonmetallized Composite Solid Propellant

Descriptive Note:

Interim rept. 1 May 1974-30 Jun 1975

Corporate Author:

MORTON THIOKOL INC HUNTSVILLE AL HUNTSVILLE DIV

Personal Author(s):

Report Date:

1975-07-01

Pagination or Media Count:

79.0

Abstract:

Monodisperse BDP combustion model was extended to nonmetallized propellants with mixed, polydisperse oxidizers by embedding monodisperse model in statistical framework including mixture ratio effects. Basically, polydisperse propellant is disassembled and rearranged to form sequence of monodisperse pseudo-propellants whose rates are computed via monodisperse model. Reassembly provides real propellants burning rate. Approach provides information pertaining to distribution of regression rates and surface structure among different size oxidizer particles. Preliminary results suggest that significant factor in rate increases wrought by introduction of small oxidizer modes is mixture ratio alternations in larger modes. Hydraulic T-burner analog was constructed and employed to visualize vent flow phenomena. Studies showed that flow enters vent with axial momentum and that momentum is partially transformed to vent into Karman vortex sheet. Fact that flow enters vent with axial momentum invalidates boundary condition of Culick analysis for flow turning gain correct boundary condition leads to null vent gain. Experimental facts consistent with proof that in formal one-dimensional flow vent gain violates second law of thermodynamics. Logical and consistent way to reduce solid rocket data when pressure-time history is not neutral was derived. Since current techniques are not self-consistent in this situation, these results open door to reclamation of performance data heretofore rejected.

Subject Categories:

  • Numerical Mathematics
  • Computer Programming and Software
  • Solid Propellant Rocket Engines
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE