DEVELOPMENT OF XM-15 ESCAPE ROCKET

reportActive / Technical Report | Accession Number: AD0814838 | Open PDF

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.

Author(s):
Macdonald, Jr, Hugh D.
Author Organization(s):
FRANKFORD ARSENAL PHILADELPHIA PA COMPONENTS ENGINEERING DIRECTORATE
Descriptive Note:
Final technical rept. Jan 1960-Mar 1963
Pagination:
0166

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
FA-R-1817, AFFDL-TR-66-162
Task Number(s):
136205
Project Number(s):
AF-1362
Monitor Series:
R-1817, TR-66-162, XA, XC
 Subject Terms
Joint Capability Areas:
JCA_3_Force Application; JCA_3.2_Engagement; JCA_3.2.1_Kinetic Means; JCA_5_Command and Control; JCA_5.3_Planning; JCA_7.2.1_Mitigate Lethal Effects; JCA_7.2_Mitigate; JCA_7_Protection; JCA_8_Building Partnerships; JCA_5.3.3_Develop Strategy; JCA_5.3.4_Develop Courses of Action; JCA_5.3.5_Analyze Courses of Action; JCA_8.2_Shape; JCA_5.5_Direct; JCA_1_Force Support; JCA_5.5.3_Establish Metrics; JCA_1.2_Force Preparation; JCA_6.1.1_Wired Transmission; JCA_6_Net Centric; JCA_8.1_Communicate; JCA_4.5.4_Requirements Definition
Modernization Areas:
Directed Energy
Communities of Interest:
Weapons Technologies
Descriptor(s):
*AEROSPACE SYSTEMS, *SOLID PROPELLANT ROCKET ENGINES, BURNING RATE, CAPTIVE TESTS, CATAPULTS, EJECTION, EJECTORS(ORDNANCE), FEASIBILITY STUDIES, FIRING TESTS(ORDNANCE), HYDROSTATICS, INSTRUMENTATION, JETTISONABLE COCKPITS, NITROCELLULOSE, PERFORMANCE(ENGINEERING), ROCKET PROPELLANT GRAINS, ROCKET PROPULSION, SLEDS, SOLID ROCKET PROPELLANTS, STRESSES, THERMAL STABILITY, THRUST
Field(s)/Group(s):
Aircraft, Solid Propellant Rocket Engines
Keyword(s):
F 104 AIRCRAFT
Report Date:
1967 Feb 01