Development and Demonstration of a Cast Propellant for the LANCE Igniter Grain.

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Abstract:

A cast composite propellant based on a HTPB binder was developed to meet the ballistic and physical requirements of the LANCE igniter grain. Formulation parameters were correlated with propellant burn rate and mechanical properties, and 1-gallon mixes were made to provide grains for a feasibility demonstration. The propellant was scaled up to a 20-gallon mixer, and grains were prepared for a prequalification demonstration task. Propellant performance in the 26-shot demonstration firing series was completely successful. The propellant is considered to be ready for qualification in the LANCE igniter.

Author(s):
Allen, Henry C. ; Cucksee, Marjorie T.
Author Organization(s):
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL ALA PROPULSION DIRECTORATE
Descriptive Note:
Technical rept.,
Pagination:
0042

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
RK-76-6
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*Surface to surface missiles, *Solid rocket propellants, *Rocket igniters, Malfunctions, Rocket propellant grains, Casting, Burning rate, Solid rocket propellant binders, Safety and arming(Ordnance)
Field(s)/Group(s):
Surface-Launched Guided Missiles, Solid Rocket Propellants
Keyword(s):
Lance missiles, MGM 52 missiles, MGM 52A missiles
Report Date:
1975 Sep 10