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Mars entry-to-landing trajectory optimization and closed loop guidanceThe guidance strategy of the Mars Rover Sample Return mission is presented in detail. Aeromaneuver versus aerobrake trades are examined, and an aerobrake analysis is presented which takes into account targeting, guidance, flight control, trajectory profile, delivery accuracy. An aeromaneuver analysis is given which includes the entry corridor, maneuver footprint, guidance, preentry phase, constant drag phase, equilibrium guide phase, variable drag phase, influence of trajectory profile on the entry flight loads, parachute deployment conditions and strategies, and landing accuracy. The Mars terminal descent phase is analyzed.
Document ID
19920060877
Document Type
Conference Paper
Authors
Ilgen, Marc R.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Manning, Raymund A.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Cruz, Manuel I.
(TRW Space and Technology Group Redondo Beach, CA, United States)
Date Acquired
August 15, 2013
Publication Date
August 1, 1991
Subject Category
Astrodynamics
Report/Patent Number
AAS PAPER 91-501
Funding Number(s)
CONTRACT_GRANT: NAS9-18141
Distribution Limits
Public
Copyright
Other
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