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P1: FHK/KXI P2: ILT/UBM/ILT AIAA [aiaaj] 15:33 22 November 2004 AI378F-03/J27142(A)/Ketsdever
 

Summary: P1: FHK/KXI P2: ILT/UBM/ILT
AIAA [aiaaj] 15:33 22 November 2004 AI378F-03/J27142(A)/Ketsdever
AIAA JOURNAL
Vol. 43, No. 1, January 2005 (Tentative)
Experimental and Numerical Determination of Micropropulsion
Device Efficiencies at Low Reynolds Numbers
Andrew D. Ketsdever
U.S. Air Force Research Laboratory, Edwards Air Force Base, California 93524
and
Michael T. Clabough,
Sergey F. Gimelshein,
and Alina Alexeenkož
University of Southern California, Los Angeles, California 90089-1191
The need for low-thrust propulsion systems for maneuvers on micro- and nanospacecraft is growing. Low-thrust
characteristics generally lead to low-Reynolds-number flows from propulsive devices that utilize nozzle expansions.
Low-Reynolds-number flows of helium and nitrogen through a small conical nozzle and a thin-walled orifice have
been investigated both numerically, using the direct simulation Monte Carlo technique, and experimentally, using
a nano-Newton thrust stand. For throat Reynolds number less than 100, the nozzle-to-orifice thrust ratio is less
than unity; however, the corresponding ratio of specific impulse remains greater than one for the Reynolds number
range from 0.02 to 200. Once the direct simulation Monte Carlo model results were verified using experimental

  

Source: Alexeenko, Alina - School of Aeronautics and Astronautics, Purdue University

 

Collections: Engineering