Accession Number:

AD0731208

Title:

Design of Propellant Fins Subjected to Axial Acceleration,

Descriptive Note:

Corporate Author:

ARMY MISSILE COMMAND REDSTONE ARSENAL ALA PROPULSION DIRECTORATE

Personal Author(s):

Report Date:

1971-08-01

Pagination or Media Count:

89.0

Abstract:

Large amounts of propellant burning surface area are required for very high acceleration missiles. Without sacrificing propellant weight, the use of large numbers of thin, solid propellant fins in recent test firings of the hypervelocity ACTION missile demonstrates a need for structural analysis to predict desirable fin configurations. A set of design charts is presented to aid in designing propellant fins for use in very high acceleration missiles. The charts show the maximum normal and maximum shear stresses encountered in propellant fin samples differing in length and web fraction when subjected to axial acceleration. Plane stress analysis and plots PSAP, a computer program combining Rohm and Haas data reduction computer program AMG067 and plane stress analysis program AMG072, is also presented. PSAP calculates stresses in a plane body and plots selected stress contours.

Subject Categories:

  • Rockets
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE