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Journal of Automation and Information Sciences
SJR: 0.275 SNIP: 0.59 CiteScore™: 0.8

ISSN Печать: 1064-2315
ISSN Онлайн: 2163-9337

Выпуски:
Том 52, 2020 Том 51, 2019 Том 50, 2018 Том 49, 2017 Том 48, 2016 Том 47, 2015 Том 46, 2014 Том 45, 2013 Том 44, 2012 Том 43, 2011 Том 42, 2010 Том 41, 2009 Том 40, 2008 Том 39, 2007 Том 38, 2006 Том 37, 2005 Том 36, 2004 Том 35, 2003 Том 34, 2002 Том 33, 2001 Том 32, 2000 Том 31, 1999 Том 30, 1998 Том 29, 1997 Том 28, 1996

Journal of Automation and Information Sciences

DOI: 10.1615/JAutomatInfScien.v35.i2.20
16 pages

Some Optimal Elementary Close to Elliptic Manoeuvres of Spacecrafts with an Engine of Constant Power and Accumulator of Energy

Boris N. Kiforenko
S.P. Timoshenko Istitute of Mechanics of National Academy of Sciences of Ukraine, Kiev, Ukraine
Yaroslav V. Tkachenko
S.P. Timoshenko Institute of Mechanics of National Academy of Sciences of Ukraine, Kiev, Ukraine

Краткое описание

We consider the problem of optimization of trajectories, controls and parameters of a propulsion system of a spacecraft, which performs manoeuvre of changing osculating parameters of an elliptic orbit. Spacecraft is equipped with the engine of low thrust with an accumulator of energy, which makes it possible to perform energy redistribution, which is generated by an onboard source of energy according to level of reactive acceleration. This provides achievement of goal of a manoeuvre with maximal value of ratio of a mass of useful load to the initial mass of the spacecraft. We consider a manoeuvre with variation of only one orbital parameter during one rotation around the centre of attraction as the elementary one. We consider motion in the Newtonian central gravity field. Optimization of controls is realized with application of the Pontryagin maximum principle. Linearized motion equations are integrated in elementary functions. Optimization of parameters of the propulsion system is performed numerically. We present results of calculations, which make it possible to estimate effectiveness of inclusion of accumulators of energy into the propulsion system of constant thrust.


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