You are here

Thermal Isolation of Solid Rocket Motor Exit Cone and Nozzle

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-13-C-7360
Agency Tracking Number: B122-027-0167
Amount: $149,998.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: MDA12-027
Solicitation Number: 2012.2
Solicitation Year: 2012
Award Year: 2013
Award Start Date (Proposal Award Date): 2012-12-11
Award End Date (Contract End Date): 2014-05-23
Small Business Information
Huntsville, AL 35811-1558
United States
DUNS: 799114574
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Daniel Butts
 Materials Engineer
 (256) 851-7653
Business Contact
 Timothy McKechnie
Title: President
Phone: (256) 851-7653
Research Institution

Current strategic solid rockets motors, such as the SM-3 third stage rocket motor (TSRM), employ highly aluminized propellants with gas temperatures of approximately 6,500F. Carbon-carbon nozzle throats and carbon cloth phenolic (CCP) exit cones are commonly used to manage the propellant exhaust. However, heat transfer from these components to the nozzle housing and exit cone bond-line joint currently limit mission profiles. This limitation is exacerbated in dual pulse motors with additional heat soak between pulses. To address this issue, a thermal barrier on the exterior exit cone and nozzle is proposed. This solution enables greater mission range and flexibility by minimizing heat transfer to the exit cone bond-line and adjacent bearing components. For dual-pulse motors, limiting the thermal soak will extend mission flexibility by allowing for a longer inter-pulse delay. During a Phase I effort, the team of Plasma Processes, Dynetics, ATK, and Aerojet will investigate the development and application of thermal barriers on CCP exit cones. Heat transfer analyses will be conducted to define effective structure and locations and estimate performance improvement. Following thermal analyses, a series of manufacturing demonstrations will be performed. Simulated TSRM nozzle sections with thermal barriers will be evaluated via high heat flux testing.

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

US Flag An Official Website of the United States Government