COOLED SOLID PROPELLANT ROCKET NOZZLES
Abstract
The feasibility of applying liquid rocket engine cooling techniques to solid rocket nozzles is being studied. Some of the more promising techniques using liquid lithium as the coolant are being investigated. Operational tests of the lithium flow co sole as embly were completed. Instrumentation of the convective cooled nozzles was completed. A stainless steel sleeve incorporating a labyrinth seal which will be used to join the instrumented nozzle to the condenser has been designed and released for procurement. The reworked spray film cooled nozzle was received and subject d to cold flow tests. Procurement of long lead time items for the spray film cooled nozzle console has begun. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 31, 1962
- Accession Number
- AD0277545
Entities
People
- Philip Wacks