FEASIBILITY DEMONSTRATION OF A ROCKET ENGINE ABLATION GAUGE
Abstract
The objective of the program is to demonstrate the feasibility of dynamically measuring ablation and erosion rates of rocket nozzle liners. The measurement technique employs trace quantities of two radioactive compounds which are embedded in the nozzle at selected locations. The compounds are chosen so that one ablates and the other erodes in the same manner as the surrounding nozzle material. Ablation and erosion depths are determined from the decrease in radiation intensity measured external to the nozzle shell. The Air Force selected a carbon phenolic, MX4926, as the nozzle material of interest for this program. Studies include analyses to establish design parameters (Task I), laboratory experiments to evaluate test variables (Task II), and five tests of a 5000-pound thrust, liquid propellant rocket engine to demonstrate the measurement technique (Task III). This report covers Task II, during which laboratory equipment was designed and built to fabricate recession sensor needles, measure incremental radiotracer uniformity along needle lenghts, and perform needle/material recession tests in an oxyacetylene flame.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1967
- Accession Number
- AD0820349
Entities
Organizations
- TRW Inc.