Accession Number:

AD0684244

Title:

COMBUSTION INSTABILITY OF SOLID PROPELLENTS: EFFECT OF OXIDIZER PARTICLE SIZE, OXIDIZER/FUEL RATIO AND ADDITION OF TITANIUM DIOXIDE TO PLASTIC PROPELLANTS

Descriptive Note:

Technical rept.

Corporate Author:

ROCKET PROPULSION ESTABLISHMENT WESCOTT (UNITED KINGDOM)

Personal Author(s):

Report Date:

1968-05-01

Pagination or Media Count:

40.0

Abstract:

The effect of variations in the composition of solid propellents on their tendency to show combustion instability at 1000 psi has been investigated using a T burner. It has been shown that ammonium perchlorate particle size can have a large effect on the acoustic response and that this is frequency- dependent. Titanium dioxide is usually added to plastic propellents to promote stable combustion and the mechanism of its action has been determined. With a view to the potential use of oxygen-balanced propellents the effect of varying the oxidizerfuel ratio of plastic propellents has also been studied.

Subject Categories:

  • Combustion and Ignition
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE