Rocket Motor - Dual Pulse

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-08-C-2004
Agency Tracking Number: F071-150-1130
Amount: $749,648.00
Phase: Phase II
Program: SBIR
Awards Year: 2008
Solitcitation Year: 2007
Solitcitation Topic Code: AF071-150
Solitcitation Number: 2007.1
Small Business Information
KNOBLEY TECHNICAL ASSOC. LLC
510 State Route 956, Rocket Center, WV, 26726
Duns: 052376147
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Louis Miltenberger
 Vice President of KTA LLC
 (304) 726-5419
 loumiltenberger@atlanticbb.net
Business Contact
 Paul Evans
Title: Vice President of KTA LLC
Phone: (304) 726-5102
Email: randjevans@atlanticbb.net
Research Institution
N/A
Abstract
The Phase II Rocket Motor-Dual Pulse program is planned to advance technologies associated with rocket motor case materials and manufacturing, propellant grain designs with burn rate augmentation, insensitive munitions compliance, thermal barrier propellant grain segregation devices, high volumetric propellant loaded case assemblies and non-eroding nozzle systems. The program consists of a design phase in which one or more candidate 7-inch diameter high performance propulsion system defined during the Phase I studies will be subjected to detailed design and ballistic performance analyses. Analysis information will be provided to the Raytheon Company to have an analytical mission performance assessment of the candidate motor(s) completed for to air-to-air missile performance. Burn rate augmentation tests will be completed using aluminized HTPE insensitive munitions propellant and an array of candidate rate augmentation materials with goals of achieving a burn rate to meet thrust goals for Pulse 2 operation using a high volumetrically loaded propellant grain. Data from these tests will then be used to design and support manufacture and testing of a full scale pulse 2 propellant grain in which the gases are exhausted over pulse 1 case insulation materials and throttled thru a non-eroding throat nozzle. The program culminates in a 7-inch diameter dual pulse motor demonstration static test firing.

* information listed above is at the time of submission.

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