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Ducted Rocket Propulsion

Report Number: AFOSR 69-2951TR p. 81-83
Author: Flemig, E. R.
Author: Flanigan, D. A.
Author: Lee, J. W.
Corporate Author: Thiokol Chemical Corporation, Huntsville Division
Date of Publication: 1969-12

The ducted rocket propulsion system combines the inherent reliability of a rocket motor with the high performance of an air breathing engine. Although this concept has been under consideration for more than 15 years, its performance potential has only been substantiated within the past two years, This paper briefly describes the evolution of the ducted rocket and the recent test data obtained under the Air Force's Ducted Rocket Technology and MINOX programs. A composite underoxidized solid propellant containing 51% boron was developed and tested under the Ducted Rocket Technology program. More than 250 direct-connect tests have been conducted with 4, 7, and 15-inch diameter motors. These studies have provided a demonstration of high combustion efficiency over a wide range of test conditions

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