DEVELOPMENT OF XM-15 ESCAPE ROCKET
Abstract
This report summarizes the design study and testing of the XM-15 Escape Rocket, a device designed to satisfy the ejection propulsion needs for a single place separable nose emergency crew escape capsule. The XM-15 was used in the feasibility testing of the separable nose escape concept, the test capsule being based on the F-104 aircraft configuration. The XM-15 Escape Rocket is designed to deliver a maximum thrust of 45,000 pounds, decreasing to 27,000 pounds at rocket burnout. The rocket's burn time is 0.50 second. The XM-15 utilizes 12 singly perforated uninhibited grains of HE-N12 propellant and was validated to operate over a temperature range of 70 + or - 20 F.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1967
- Accession Number
- AD0814838
Entities
People
- Hugh D. Macdonald Jr.