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Powdered Propellant Rocket Motor

Award Information

Department of Defense
Award ID:
Program Year/Program:
2013 / SBIR
Agency Tracking Number:
Solicitation Year:
Solicitation Topic Code:
Solicitation Number:
Small Business Information
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
Phase 1
Fiscal Year: 2013
Title: Powdered Propellant Rocket Motor
Agency: DOD
Contract: HQ0147-13-C-7311
Award Amount: $99,999.00


The preliminary design of a DAC motor using a powdered solid propellant, injected as an aerosol into the combustion chamber in a controlled manner, is formulated in this program. The injection methodology is based on a recent design developed for injecting nano and micron sized powdered metallic fuel into a scramjet combustion chamber. A variant of this design will be constructed and tested in this program, providing key data needed for the CFD-based design studies, such as percentage of powdered propellant that can be carried by the aerosol and how this varies with particle properties. The burning characteristics of the powdered propellant, which will be dependant on the size and shape of the particles as well as its composition, will be determined by laboratory studies, yielding the burn rate data needed by the CFD for motor design. CFD studies will be performed using advanced models that have been applied to analyze a variety of particulate combustion problems. The dependence of motor performance on the key parameters (such as the injected aerosol mass flux, the size of the particles, etc.) will be established, and a preliminary DAC motor design will be formulated which meets nominal performance standards.

Principal Investigator:

Sanford M. Dash
Chief Scientist&President
(215) 766-1520

Business Contact:

Brian J. York
Principal Scientist&Treasurer
(215) 766-1520
Small Business Information at Submission:

Combustion Research and Flow Technology, Inc.
6210 Kellers Church Road Pipersville, PA -

EIN/Tax ID: 232759059
Number of Employees:
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No