Accession Number : ADD014119

Title :   Process for Assessing the Effect of Propellant Strain on Propellant Burn Rate.

Descriptive Note : Patent, Filed 13 Oct 87, patented 28 Mar 89,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Bonadies, Gary N ; O'Clair, Mark ; Parry, David W

Report Date : 28 Mar 1989

Pagination or Media Count : 4

Abstract : The present invention describes a process for relating burn rate in a sample propellant to a strain field imposed therein by bending the sample propellant by a determined amount. The propellant is cast upon an initially flat plate having a single pair of fixed parallel walls. The plate is bent parallel to the walls before the test burn. Measurement of thickness of the propellant before the burn and after the burn are related to the strain placed in the propellant by the bending. All measurements occur when the plate is flat. Keywords: Solid rocket propellants; Patents. (kt)

Descriptors :   *BURNING RATE, *PATENTS, *SOLID ROCKET PROPELLANTS, BENDING, FLAT PLATE MODELS, MEASUREMENT, STRAIN(MECHANICS), PARALLEL ORIENTATION, PROPELLANT BURN OUT, PROPELLANTS, THICKNESS, WALLS

Subject Categories : Solid Rocket Propellants
      Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE