Autonomous multi satellites assembly in keplerian orbits

In this paper, the guidance and control algorithms of an autonomous multiple satellite assembly are developed in a general keplerian orbit. The guidance algorithms are based on defining the velocity profile of each satellite in two different segment of space. In the first segment, the guidance law u...

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Main Authors:	Okasha, Mohamed Elsayed Aly Abd Elaziz, Park, Chandeok, Park, Sang-Young
Format:	Conference or Workshop Item
Language:	English
Published:	American Institute of Aeronautics and Astronautics 2013
Subjects:	TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering
Online Access:	http://irep.iium.edu.my/38417/ http://irep.iium.edu.my/38417/ http://irep.iium.edu.my/38417/ http://irep.iium.edu.my/38417/1/Autonomous_Multi_Satellites_Assembly_in_Keplerian_Orbits.pdf

id	iium-38417
recordtype	eprints
spelling	iium-384172014-10-01T04:25:54Z http://irep.iium.edu.my/38417/ Autonomous multi satellites assembly in keplerian orbits Okasha, Mohamed Elsayed Aly Abd Elaziz Park, Chandeok Park, Sang-Young TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering In this paper, the guidance and control algorithms of an autonomous multiple satellite assembly are developed in a general keplerian orbit. The guidance algorithms are based on defining the velocity profile of each satellite in two different segment of space. In the first segment, the guidance law utilizes the analytical closed form solution of the satellite relative motion in close proximity in which the gravitational forces are considered. To avoid the singularity associated with the analytical solution, switching to the second segment of space is introduced to redefine the velocity profile as a function of the relative distance between satellites and relative distance to the desired goal location in the assembly. The guidance algorithms suggest attraction and repulsion forces between the individuals in which the attraction forces dominate on large distances while repulsion forces dominate on close distances. The Proportional-Derivative (PD) continuous feedback control and the velocity change Δv control algorithms are presented to perform efficient fuel consumption maneuver, while avoiding collisions and to track the guidance trajectories. Numerical simulations are performed to assess the precision of these algorithms in hexagonal and cubic formation assembly. American Institute of Aeronautics and Astronautics 2013 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/38417/1/Autonomous_Multi_Satellites_Assembly_in_Keplerian_Orbits.pdf Okasha, Mohamed Elsayed Aly Abd Elaziz and Park, Chandeok and Park, Sang-Young (2013) Autonomous multi satellites assembly in keplerian orbits. In: AIAA Guidance, Navigation, and Control (GNC) Conference, 19-22 August 2013, Boston, Massachusetts. http://arc.aiaa.org/doi/abs/10.2514/6.2013-5195 10.2514/6.2013-5195
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering
spellingShingle	TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering Okasha, Mohamed Elsayed Aly Abd Elaziz Park, Chandeok Park, Sang-Young Autonomous multi satellites assembly in keplerian orbits
description	In this paper, the guidance and control algorithms of an autonomous multiple satellite assembly are developed in a general keplerian orbit. The guidance algorithms are based on defining the velocity profile of each satellite in two different segment of space. In the first segment, the guidance law utilizes the analytical closed form solution of the satellite relative motion in close proximity in which the gravitational forces are considered. To avoid the singularity associated with the analytical solution, switching to the second segment of space is introduced to redefine the velocity profile as a function of the relative distance between satellites and relative distance to the desired goal location in the assembly. The guidance algorithms suggest attraction and repulsion forces between the individuals in which the attraction forces dominate on large distances while repulsion forces dominate on close distances. The Proportional-Derivative (PD) continuous feedback control and the velocity change Δv control algorithms are presented to perform efficient fuel consumption maneuver, while avoiding collisions and to track the guidance trajectories. Numerical simulations are performed to assess the precision of these algorithms in hexagonal and cubic formation assembly.
format	Conference or Workshop Item
author	Okasha, Mohamed Elsayed Aly Abd Elaziz Park, Chandeok Park, Sang-Young
author_facet	Okasha, Mohamed Elsayed Aly Abd Elaziz Park, Chandeok Park, Sang-Young
author_sort	Okasha, Mohamed Elsayed Aly Abd Elaziz
title	Autonomous multi satellites assembly in keplerian orbits
title_short	Autonomous multi satellites assembly in keplerian orbits
title_full	Autonomous multi satellites assembly in keplerian orbits
title_fullStr	Autonomous multi satellites assembly in keplerian orbits
title_full_unstemmed	Autonomous multi satellites assembly in keplerian orbits
title_sort	autonomous multi satellites assembly in keplerian orbits
publisher	American Institute of Aeronautics and Astronautics
publishDate	2013
url	http://irep.iium.edu.my/38417/ http://irep.iium.edu.my/38417/ http://irep.iium.edu.my/38417/ http://irep.iium.edu.my/38417/1/Autonomous_Multi_Satellites_Assembly_in_Keplerian_Orbits.pdf
first_indexed	2023-09-18T20:55:12Z
last_indexed	2023-09-18T20:55:12Z
_version_	1777410257466687488

Autonomous multi satellites assembly in keplerian orbits

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