Accession Number:

AD0368628

Title:

DEMONSTRATION OF A SINGLE-CHAMBER DUAL-THRUST MOTOR,

Descriptive Note:

Corporate Author:

REDSTONE ARSENAL RESEARCH DIV ROHM AND HAAS CO HUNTSVILLE ALA

Personal Author(s):

Report Date:

1966-01-12

Pagination or Media Count:

55.0

Abstract:

A combination slotted-tube end-burning charge configuration was used to achieve a boost-to-sustain thrust ratio of about 20 in a single chamber motor assembly. The grain was cast in place with a single propellant formulation. Test firings were carried out with both plastisol nitrocellulose composite and HC binder composite propellants containing 1 aluminum. These tests demonstrated rapid and smooth transitions from the high to the low levels of operation with pressure ratios up to 17. No indication of quenching or combustion instability occurred with transitions from over 2000 psia to as low as 120 psia. Operational capabilities over the temperature range -40 F to 140 F were demonstrated with successful firings of the composite propellant rounds. The plastisol charges failed at temperatures of -40 F. Motors containing both plastisol and composite propellants were successfully cycled between these temperatures and withstood extended periods of cold soaking at -40 F. Charges of both propellants were successfully subjected to acceleration forces which were by a factor of two greater than would normally be experienced in a proposed application. Author

Subject Categories:

  • Rocket Engines
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE