COMBUSTION TAILORING CRITERIA FOR SOLID PROPELLANTS.
Abstract
The objective of this research program is to develop an analytical model describing the steady-state combustion of solid propellants which is suitably equipped to provide combustion tailoring criteria for both state-of-the-art and advanced propellant formations. Tests with small samples of propellants will provide experimental data for modeling the propellant combustion process for different ingredient variations. Additional tests simulating the environment of a rocket motor will provide experimental data showing the effect of rocket motor environment upon the combustion process. During Phase III, work was directed toward developing the analytical model and modifying aspects of the model. A list of propellants was chosen for study in tests to be conducted during the remainder of the research program. Small samples of a CTPB/AP propellant were burned in a pressurized combustion bomb and extinguished by rapid depressurization of the bomb. The surface structure was examined through a 10X - 80X microscope. Results from tests conducted in apparatus simulating the environment of a rocket motor (slab combustor) and using a CTPB/AP/A1 propellant showed that the thermal environment of the combustor reaches a maximum level at 200 psia. To learn what effect the thermal environment has upon the propellant burning rate, a technique was developed to directly measure burning rate in the slab combustor. The approach uses a high-speed camera to record the movement of the propellant burning surface with respect to a reference scale.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1968
- Accession Number
- AD0391759
Entities
People
- M. W. Beckstead
- Ronald L. Derr
Organizations
- Lockheed Propulsion Company