Slow Cook-Off Insensitive Munitions Solutions for Solid Rocket Motors

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-09-C-7037
Agency Tracking Number: B073-047-0449
Amount: $1,754,290.00
Phase: Phase II
Program: SBIR
Awards Year: 2009
Solicitation Year: 2007
Solicitation Topic Code: MDA07-047
Solicitation Number: 2007.3
Small Business Information
1832 180th St. SE, Bothell, WA, 98012
DUNS: 086581902
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Hunter Golden
 Sr. Mechnical Engineer
 (425) 487-4020
Business Contact
 Tom Prenzlow
Title: President
Phone: (425) 487-4020
Research Institution
A major MDA thrust area is the development of highly reliable technologies for Insensitive Munition (IM) compliance for Large Diameter Solid Rocket Motors (SRM) subjected to slow cook-off. Federal law requires all munitions to be as IM compliant as is practicable. Currently no solution exists for slow cook-off that reduces the reaction violence or allows the large diameter solid rocket motors to achieve only a burning reaction. Systima’s design concept thermally activates a case venting system for large diameter rocket motors during IM Slow Cook-off. The case severance/venting system provides the necessary initial venting to significantly reduce internal pressure thus reducing chances of violent slow cook-off reactions. Systima will partner with ATK-Tactical Propulsion and Controls Division (Elkton, MD) and Corvid Technologies to design, build, and test the SRM Case Severance System. ATK will provide technical information for system integration and representative motor hardware for concept demonstration tests including a live motor slow cook-off test per MIL-STD-2105C. Corvid will provide design requirement and performance estimates based on a developmental model that predicts the thermal state throughout a solid rocket motor versus time in a slow cook-off environment and how that affects the eventual build up to reaction in the propellant.

* Information listed above is at the time of submission. *

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