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Preliminary design of a long-endurance Mars aircraftThe preliminary design requirements of a long endurance aircraft capable of flight within the Martian environment was determined. Both radioisotope/heat engine and PV solar array power production systems were considered. Various cases for each power system were analyzed in order to determine the necessary size, weight and power requirements of the aircraft. The analysis method used was an adaptation of the method developed by Youngblood and Talay of NASA-Langley used to design a high altitude earth based aircraft. The analysis is set up to design an aircraft which, for the given conditions, has a minimum wingspan and maximum endurance parameter. The results showed that, for a first approximation, a long endurance aircraft is feasible within the Martian environment. The size and weight of the most efficient solar aircraft were comparable to the radioisotope powered one.
Document ID
19900012447
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Colozza, Anthony J. (Sverdrup Technology, Inc. Brook Park, OH, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2000
NAS 1.26:185243
NASA-CR-185243
E-5475
Meeting Information
Meeting: Joint Propulsion Conference
Location: Orlanda, FL
Country: United States
Start Date: July 16, 1990
End Date: July 18, 1990
Sponsors: SAE, ASEE, AIAA, ASME
Accession Number
90N21763
Funding Number(s)
CONTRACT_GRANT: NAS3-25266
PROJECT: RTOP 591-11-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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