COOLED SOLID PROPELLANT ROCKET NOZZLES
Abstract
The feasibility of applying liquid rocket engine cooling techniques to solid rocket nozzles was studied. Some of the more promising techniques include using liquid Li as the coolant. The nozzle to motor case adaptor design was completed. The spray film cooled nozzle was secured from the vendor and subjected to cold flow tests. Setup of the lithium flow system console and the control panel were completed. Preliminary tests of the instrumentation, controls and heating circuits were started. A summary of data derived from the literature on cooled solid rocket nozzles is presented. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 30, 1961
- Accession Number
- AD0265606
Entities
People
- R.h. Alper