Mathematics of attitude-constrained optimal low-thrust orbit transfer

Aerotecnica Missili & Spazio

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Field Value
 
Title Mathematics of attitude-constrained optimal low-thrust orbit transfer
 
Creator Kéchichian, Jean Albert
 
Subject


 
Description The mathematics of the problem of optimal low-thrust transfer with constant exhaust velocity, in which the instan-taneous thrust direction is constrained in roll is presented. Thus only pitch and yaw are free while roll is held constantat zero. This attitude-constrained transfer mode allows the practitioners to carry out trade-o analyses between RCS(Reaction Control System) propellant and main propulsion system propellant expenditure. Snap-roll maneuvers neededto orient the solar panels normal to the sun can be eliminated, saving RCS propellant at the expense of additional transferV and time, due to the inability to orient the panels normal to the sun, which results in reduced power output, andtherefore, thrust.This constrained case extends previous analyses of the optimal solution for the minimum-time low-thrust transfer,namely the unconstrained thrust direction case, and the zero pitch case. The thrust vector specication requires thespecication of two polar angles in three-dimensional space, and the optimal panel orientation angle is now a functionof these two control angles which are derived themselves from the optimality conditions.The optimal panel orientation angle in terms of the thrust vector orientation, for maximum power output, is derivedfor both the pitch-yaw and yaw-pitch sequences.
 
Publisher Associazione Italiana di Aeronautica e Astronautica (AIDAA)
 
Contributor
 
Date 2018-02-11
 
Type info:eu-repo/semantics/article
info:eu-repo/semantics/publishedVersion
Peer-reviewed Article

 
Format application/pdf
 
Identifier http://131.114.27.37/index.php/AMS/article/view/326
10.19249/ams.v96i4.326
 
Source Aerotecnica Missili & Spazio; Vol 96, No 4 (2017); 180-194
0365-7442
 
Language eng
 
Relation http://131.114.27.37/index.php/AMS/article/view/326/294
 
Rights Copyright (c) 2018 Aerotecnica Missili & Spazio
 

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