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Dynamics, control and reconfiguration of satellite formation flight around Lagrangian points

Grant number: 13/03233-6
Support type:Scholarships in Brazil - Post-Doctorate
Effective date (Start): November 01, 2013
Effective date (End): October 31, 2017
Field of knowledge:Engineering - Aerospace Engineering
Principal researcher:Othon Cabo Winter
Grantee:Francisco Javier Tipán Salazar
Home Institution: Faculdade de Engenharia (FEG). Universidade Estadual Paulista (UNESP). Campus de Guaratinguetá. Guaratinguetá , SP, Brazil
Associated research grant:11/08171-3 - Orbital dynamics of minor bodies, AP.TEM
Associated scholarship(s):15/00559-3 - Intervening on Earth's climate through heliotropic dust rings and dust cloud at the L1 Lagrange point, BE.EP.PD

Abstract

The concept of Satellite Formation Flying (SFV) means having two or more satellites in orbit, with their relative positions remain constant or obeying a configuration eventually dynamics along the trajectory This concept involves control over the movement of a group of vehicles, with the goal of maintaining a certain geometry configuration between the elements of the set. It allows a group of small and cheap satellites operating like a single "virtual large satellite" , providing an ability to obtain unique data. Thus, using the Earth-Moon system, this project aims to present a methodology that meets the desired effectiveness and efficiency, supported by the concepts from the application of the Theory of Dynamical Systems and exploitation of the unique features of the Circular Restricted Three Body Problem, basic model for the scenario Earth-Moon-particle, where the gravitational iterations between the Satellites in Formation Flight are neglected. In this project, the satellites are located around the L4 and L5 Lagrangian points which form an equilateral triangles with the Earth and the Moon. In Earth-Moon system, L4 and L5 are stable equilibrium points (centers), i.e there exist a family of periodic orbits around them. It is therefore necessary to find an optimal control strategy for Satellites in Formation Flight to keep fixed the configuration in the direction in which it is more stable. Finally, depending on the type of applications, such as space telescopes may be necessary to reconfigure the geometrical arrangement of the formation. We must therefore find a set of maneuvers that minimize the spent fuel to change the geometry and avoid collision between the satellites. (AU)

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Scientific publications (9)
(References retrieved automatically from Web of Science and SciELO through information on FAPESP grants and their corresponding numbers as mentioned in the publications by the authors)
SALAZAR, F. J. T.; WINTER, O. C.; MCINNES, C. R. Collecting solar power by formation flying systems around a geostationary point. COMPUTATIONAL & APPLIED MATHEMATICS, v. 37, n. 1, SI, p. 84-95, DEC 2018. Web of Science Citations: 1.
SALAZAR, F. J. T.; MCINNES, C. R.; WINTER, O. C. Periodic orbits for space-based reflectors in the circular restricted three-body problem. CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY, v. 128, n. 1, p. 95-113, MAY 2017. Web of Science Citations: 5.
SALAZAR, F. J. T.; MCINNES, C. R.; WINTER, O. C. Intervening in Earth's climate system through space-based solar reflectors. Advances in Space Research, v. 58, n. 1, p. 17-29, JUL 1 2016. Web of Science Citations: 6.
SALAZAR, F. J. T.; WINTER, O. C.; MACAU, E. E.; MASDEMONT, J. J.; GOMEZ, G. Zero drift regions and control strategies to keep satellite in formation around triangular libration point in the restricted Sun-Earth-Moon scenario. Advances in Space Research, v. 56, n. 7, p. 1502-1518, OCT 1 2015. Web of Science Citations: 3.
SALAZAR, F. J. T.; WINTER, O. C.; MACAU, E. E.; MASDEMONT, J. J.; GOMEZ, G. Natural formations at the Earth-Moon triangular point in perturbed restricted problems. Advances in Space Research, v. 56, n. 1, p. 144-162, JUL 1 2015. Web of Science Citations: 5.
SALAZAR, F. J. T.; MACAU, E. E. N.; WINTER, O. C. Pareto Frontier for the time-energy cost vector to an Earth-Moon transfer orbit using the patched-conic approximation. COMPUTATIONAL & APPLIED MATHEMATICS, v. 34, n. 2, p. 461-475, JUL 2015. Web of Science Citations: 4.
SALAZAR, F. J. T.; MACAU, E. E. N.; WINTER, O. C. Chaotic Dynamics in a Low-Energy Transfer Strategy to the Equilateral Equilibrium Points in the Earth-Moon System. INTERNATIONAL JOURNAL OF BIFURCATION AND CHAOS, v. 25, n. 5 MAY 2015. Web of Science Citations: 3.
SALAZAR, F. J. T.; MASDEMONT, J. J.; GOMEZ, G.; MACAU, E. E.; WINTER, O. C. Zero, minimum and maximum relative radial acceleration for planar formation flight dynamics near triangular libration points in the Earth-Moon system. Advances in Space Research, v. 54, n. 9, p. 1838-1857, NOV 1 2014. Web of Science Citations: 5.
SALAZAR, F. J. T.; MACAU, E. E. N.; WINTER, O. C. Alternative transfer to the Earth-Moon Lagrangian points L4 and L5 using lunar gravity assist. Advances in Space Research, v. 53, n. 3, p. 543-557, FEB 1 2014. Web of Science Citations: 7.

Please report errors in scientific publications list by writing to: cdi@fapesp.br.