TY - GEN
T1 - A systems engineering approach to the conceptual design of a martian UAV
AU - Tsai, Kyle
AU - Chadha, Parul
AU - D’Urso, Steven J.
AU - Hilton, Harry H.
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - A special project group formed in 2014 at University of Illinois at Urbana-Champaign performed systems engineering study of the potential application of an unmanned aerial vehicle to augment the exploration capabilities of land-based Martian vehicles. This group worked under the guidance of members of NASA’s Human Exploration team at Johnson Space Center. The suggested study is a follow up to the Mars surface systems study [3]. The systems engineering approach used to achieve a conceptual design of its configuration and operations is documented in the report, A Conceptual Design of a Martian UAV [1] and is summarized in this paper. Total systems contexts were explored and defined using mission objectives and vignettes inspired by the three science mission areas prescribed in the Mars Design Reference Architecture 5.0 (DRA 5.0): surface mapping, atmospheric, and biological investigations. Systems level capability requirements were derived from operational ranges and covereages defined by recommended surface landing sites in DRA 5.0. Mission systems, navigation, avionic, power and propulsion systems architectures were allocated, and the air vehicle configuration candidates selected. Atmospheric modeling for performance and risk assessments were some of the discriminators used in the down selection process.
AB - A special project group formed in 2014 at University of Illinois at Urbana-Champaign performed systems engineering study of the potential application of an unmanned aerial vehicle to augment the exploration capabilities of land-based Martian vehicles. This group worked under the guidance of members of NASA’s Human Exploration team at Johnson Space Center. The suggested study is a follow up to the Mars surface systems study [3]. The systems engineering approach used to achieve a conceptual design of its configuration and operations is documented in the report, A Conceptual Design of a Martian UAV [1] and is summarized in this paper. Total systems contexts were explored and defined using mission objectives and vignettes inspired by the three science mission areas prescribed in the Mars Design Reference Architecture 5.0 (DRA 5.0): surface mapping, atmospheric, and biological investigations. Systems level capability requirements were derived from operational ranges and covereages defined by recommended surface landing sites in DRA 5.0. Mission systems, navigation, avionic, power and propulsion systems architectures were allocated, and the air vehicle configuration candidates selected. Atmospheric modeling for performance and risk assessments were some of the discriminators used in the down selection process.
UR - http://www.scopus.com/inward/record.url?scp=85007500701&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85007500701&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85007500701
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)
T2 - 54th AIAA Aerospace Sciences Meeting, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -