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Martian Aerocapture Terminal Point Guidance: A Reference Path Optimization StudyAn effective method of terminal point guidance is to employ influence coefficients, which are solved from a set of differential equations adjoint to the linearized perturbations of the equations of motion about a reference trajectory. Hence, to optimize this type of guidance, one must first optimize the reference trajectory that the guidance is based upon. This study concentrates on various methods to optimize a reference trajectory for a Martian aerocapture maneuver, including a parametric analysis and first order gradient method. Resulting reference trajectories were tested in separate 2000 6-DOF Monte Carlo runs, using the Atmospheric Guidance Algorithm Testbed for the Mars Surveyor Program 2001 (MSP '01) Orbiter. These results were compared to an August 1998 study using the same terminal point control guidance algorithm and simulation testbed. Satisfactory improvements over the 1998 study are amply demonstrated.
Document ID
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Ro, Theodore U.
(NASA Johnson Space Center Houston, TX United States)
Queen, Eric M.
(NASA Langley Research Center Hampton, VA United States)
Striepe, Scott A.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 19, 2013
Publication Date
May 1, 1999
Publication Information
Publication: 1999 Flight Mechanics Symposium
Subject Category
Distribution Limits
Work of the US Gov. Public Use Permitted.
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