TY - GEN
T1 - Development of 10 inch diameter titanium rolling metal diaphragm tank for green propellant
AU - Conomos, Harry
AU - Alongi, Christopher G.
AU - Yager, Jacqueline
AU - Goddard, Richard A.
AU - Salzler, Todd J.
AU - Fetes, James P.
AU - Burch, Keith J.
AU - Moore, Jeffery D.
N1 - Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2017
Y1 - 2017
N2 - This paper will discuss the design and test results of a 10-inch diameter titanium propellant tank with a Rolling Metal Diaphragm (RMD) used as a propellant expulsion device, as well as the subsequent delivery of a 10 inch diameter titanium RMD propellant tank for a flight system. Moog Inc. provided internal funding in order to expand its heritage flight qualified aluminum RMD tank designs using materials compatible with green propellants, such as LMP-103S and AFM-315E. Advantages of a metal diaphragm tank include a sealed, all welded design, no slosh or other transient dynamic response, predictable center of gravity, and near zero permeability. These tanks utilize a diaphragm with a simple initial shape, and conforming the outlet shell to match the final contour of the diaphragm, thereby providing high expulsion efficiency of ≥ 98 %.
AB - This paper will discuss the design and test results of a 10-inch diameter titanium propellant tank with a Rolling Metal Diaphragm (RMD) used as a propellant expulsion device, as well as the subsequent delivery of a 10 inch diameter titanium RMD propellant tank for a flight system. Moog Inc. provided internal funding in order to expand its heritage flight qualified aluminum RMD tank designs using materials compatible with green propellants, such as LMP-103S and AFM-315E. Advantages of a metal diaphragm tank include a sealed, all welded design, no slosh or other transient dynamic response, predictable center of gravity, and near zero permeability. These tanks utilize a diaphragm with a simple initial shape, and conforming the outlet shell to match the final contour of the diaphragm, thereby providing high expulsion efficiency of ≥ 98 %.
UR - https://www.scopus.com/pages/publications/85086919027
UR - https://www.scopus.com/pages/publications/85086919027#tab=citedBy
U2 - 10.2514/6.2017-4915
DO - 10.2514/6.2017-4915
M3 - Conference contribution
AN - SCOPUS:85086919027
SN - 9781624105111
T3 - 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
BT - 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
Y2 - 10 July 2017 through 12 July 2017
ER -