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Modification of an impulse-factoring orbital transfer technique to account for orbit determination and maneuver execution errorsA method has previously been developed to satisfy terminal rendezvous and intermediate timing constraints for planetary missions involving orbital operations. The method uses impulse factoring in which a two-impulse transfer is divided into three or four impulses which add one or two intermediate orbits. The periods of the intermediate orbits and the number of revolutions in each orbit are varied to satisfy timing constraints. Techniques are developed to retarget the orbital transfer in the presence of orbit-determination and maneuver-execution errors. Sample results indicate that the nominal transfer can be retargeted with little change in either the magnitude (Delta V) or location of the individual impulses. Additonally, the total Delta V required for the retargeted transfer is little different from that required for the nominal transfer. A digital computer program developed to implement the techniques is described.
Document ID
19740018178
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Kibler, J. F. (NASA Langley Research Center Hampton, VA, United States)
Green, R. N. (NASA Langley Research Center Hampton, VA, United States)
Young, G. R. (NASA Langley Research Center Hampton, VA, United States)
Kelly, M. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Space Sciences
Report/Patent Number
L-9280
NASA-TM-X-2971
Accession Number
74N26291
Funding Number(s)
PROJECT: RTOP 790-93-08-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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