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Entry Attitude Controller for the Mars Science LaboratoryThis paper describes the preliminary concept for the RCS 3-axis attitude controller for the exo-atmospheric and guided entry phases of the Mars Science Laboratory Entry, Descend and Landing. The entry controller is formulated as three independent channels in the control frame, which is nominally aligned with the stability frame. Each channel has a feedfoward and a feedback. The feedforward path enables fast response to large bank commands. The feedback path stabilizes the vehicle angle of attack and sideslip around its trim position, and tracks bank commands. The feedback path has a PD/D structure with deadbands that minimizes fuel usage. The performance of this design is demonstrated via simulation.
Document ID
20070034767
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Brugarolas, Paul B.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
SanMartin, A. Miguel
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Wong, Edward C.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
August 24, 2013
Publication Date
March 3, 2007
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
IEEEAC 1500, Version 3
Meeting Information
Meeting: IEEE Aerospace Conference
Location: Big Sky, MT
Country: United States
Start Date: March 3, 2007
End Date: March 10, 2007
Sponsors: Institute of Electrical and Electronics Engineers
Distribution Limits
Public
Copyright
Other
Keywords
Mars
aerodynamics
Entry, Descent, Landing (EDL)
control systems

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