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Optimal dual-fuel propulsion for minimum inert weight or minimum fuel costAn analytical investigation of single-stage vehicles with multiple propulsion phases has been conducted with the phasing optimized to minimize a general cost function. Some results are presented for linearized sizing relationships which indicate that single-stage-to-orbit, dual-fuel rocket vehicles can have lower inert weight than similar single-fuel rocket vehicles and that the advantage of dual-fuel vehicles can be increased if a dual-fuel engine is developed. The results also indicate that the optimum split can vary considerably with the choice of cost function to be minimized.
Document ID
19740028518
Document Type
Conference Paper
Authors
Martin, J. A.
(NASA Langley Research Center Space Systems Div., Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1973
Subject Category
Space Vehicles
Report/Patent Number
AIAA PAPER 73-1246
Meeting Information
Propulsion Conference(Las Vegas, NV)
Distribution Limits
Public
Copyright
Other
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