Accession Number:

AD0814838

Title:

DEVELOPMENT OF XM-15 ESCAPE ROCKET

Descriptive Note:

Final technical rept. Jan 1960-Mar 1963

Corporate Author:

FRANKFORD ARSENAL PHILADELPHIA PA COMPONENTS ENGINEERING DIRECTORATE

Personal Author(s):

Report Date:

1967-02-01

Pagination or Media Count:

166.0

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 rockets 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.

Subject Categories:

  • Aircraft
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE