Accession Number:

AD0871583

Title:

Improved Design Procedures for Thrust Termination of Solid Propellant Motors

Descriptive Note:

Final rept. 1 Feb 1969-1 Feb 1970

Corporate Author:

BRIGHAM YOUNG UNIV PROVO UT DEPT OF CHEMICAL ENGINEERING

Personal Author(s):

• Coates, Ralph L.
• Horton, M. Duane

Report Date:

1970-05-01

Pagination or Media Count:

114.0

Abstract:

The objective of this project was to carry out both experimental and analytical studies leading to improved design procedures for predicting thrust termination of single-chamber controllable solid motors. The experimental work consisted of measuring quantitatively the effects of incident thermal radiation on low pressure burning rates and deflagration limits of typical solid propellants. A technique was developed in which small cylindrical samples of the propellant were burned inside an electrically heated tube furnace. At furnace wall temperatures corresponding to the interior surfaces of a rocket motor, the burning rates were observed to be as much as 50 greater at 10psia than they were when measured in the conventional strand burner configuration. Analytical work was performed using an improved mathematical model of the transient combustion process of a solid propellant.

Descriptors:

• *CONTROLLABLE THRUST ROCKET ENGINES
• *SOLID PROPELLANT ROCKET ENGINES
• *THRUST TERMINATION SYSTEMS
• BURNING RATE
• COMBUSTION
• COMPUTER PROGRAMS
• EXPERIMENTAL DATA
• INTERIOR BALLISTICS
• LEAST SQUARES METHOD
• MATHEMATICAL MODELS
• NOZZLE AREA RATIO
• NOZZLE THROATS
• THERMAL RADIATION

Subject Categories:

• Solid Propellant Rocket Engines
• Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE