Preliminary design of a long-endurance Mars aircraft
- Colozza, Anthony J.
- Apr 1, 1990.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
- The 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.
- Other Subject(s):
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19900012447.
Accession ID: 90N21763.
AIAA PAPER 90-2000.
Joint Propulsion Conference; 16-18 Jul. 1990; Orlanda, FL; United States.
- No Copyright.
View MARC record | catkey: 15686616