Magazine Article

Thermal Design and Analysis of a Rocket-Engine TAN Injector

TBMG-4554

02/01/2007

Abstract
Content

A subscale thrust-augmented-nozzle (TAN) rocket engine was designed, built, and hot-fire tested to demonstrate the validity of the TAN concept. As described in more detail in the immediately preceding article, in a TAN, during operation at sea level, thrust is augmented through injection and burning of secondary propellants (a fuel and an oxidizer) within the nozzle, downstream of the nozzle throat. The secondary propellants can be the same as, or different from, the primary propellants (the fuel and oxidizer burned during operation, in a near vacuum, in the absence of thrust augmentation).

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Citation
"Thermal Design and Analysis of a Rocket-Engine TAN Injector," Mobility Engineering, February 1, 2007.
Additional Details
Publisher
Published
Feb 1, 2007
Product Code
TBMG-4554
Content Type
Magazine Article
Language
English