Rocket Motor Igniter for Precision Centroid of Thrust.

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Abstract:

An igniter for use in a rocket having a predetermined spin rate during flight. The rocket includes a plurality of motors facing out from the body of the rocket and each motor is fired in a predetermined sequence. The igniter includes a squib for igniting fine black powder in the cavity of the igniter. The powder is packed in the cavity of the igniter with the density substantially like a cake. A cover member retains the powder in the cavity for a sufficient time to achieve fast ignition. Author

Author(s):
Betts, Robert E. ; Williams, Nathan P.
Author Organization(s):
DEPARTMENT OF THE ARMY WASHINGTON DC
Descriptive Note:
Patent Application,
Pagination:
0008

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Availability: This Government-owned Invention Available For U.s. Licensing And, Possibly, For Foreign Licensing. Copy Of Application Available Ntis.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
PAT-APPL-218 597
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means
Communities of Interest:
Weapons Technologies
Descriptor(s):
*Patent applications, *Rocket igniters, *Rocket engines, Thrust vector control systems, Precision, Spinning(Motion), Electric igniters, Electric primers, Inventions
Field(s)/Group(s):
Rocket Engines
Keyword(s):
Precision centroid thrusts
Report Date:
1980 Dec 19