Accession Number:

ADB211864

Title:

Studies of Ablative Material Performance for Solid Rocket Nozzle Applications

Descriptive Note:

Final rept.

Corporate Author:

AEROTHERM CORP MOUNTAIN VIEW CA

Report Date:

1968-03-01

Pagination or Media Count:

174.0

Abstract:

Analytical and experimental studies of ablative material performance for solid rocket nozzle applications were performed. Large scale computer codes were employed to calculate the ablation, thermal, and structural responses of the 260-SL-3 nozzle as a design check and as a basis for post- fire analysis. The calculated performance included consideration of surface chemical reactions, melt removal, particle deposition, char swelling, in-depth kinetic decomposition, and anisotropic mechanical and thermal Properties. Laboratory tests were performed to determine and study the properties and performance mechanisms of three silica phenolic materials - MX2600, MX2600-96, and MXS-ll3. In performing these tests, an arc plasma generator was used to simulate the solid rocket nozzle environment and a two-dimensional nozzle was used to simulate a large ablative part. The results included the definition of the surface melt removal characteristics and the thermal conductivity of the charring material to 5,000 deg R for O deg and 90 deg layup angles. Ablative and thermal performance calculations were also performed for the nozzle of an upper-stage restartable beryllium propellant motor.

Subject Categories:

  • Miscellaneous Materials
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE