@InCollection{RomeroSouz:2019:SaCoSy,
author = "Romero, Alessandro Gerlinger and Souza, Luiz Carlos Gadelha de",
title = "Satellite controller system based on reaction wheels using the
State-Dependent Riccati Equation (SDRE) on Java",
booktitle = "Proceedings of the 10th International Conference on Rotor Dynamics
- IFToMM",
publisher = "Springer",
year = "2019",
editor = "Cavalca, Katia Lucchesi and Weber, Hans Ingo",
pages = "547--561",
keywords = "Nonlinear control · SDRE · Satellite · Attitude Reaction wheels.",
abstract = "Complex space missions involving large angle maneuvers and fast
attitude control require nonlinear control methods to design the
Satellite Controller System (SCS) in order to satisfy robustness
and performance requirements. One candidate method for a nonlinear
SCS control law is the State-Dependent Riccati Equation (SDRE).
SDRE provides an effective algorithm for synthesizing nonlinear
feedback control by allowing nonlinearities in the system states
while offering great design flexibility through state-dependent
weighting matrices. In that context, analysis by simulation of
nonlinear control methods can save money and time. Although,
commercial 3D simulators exist that can accommodate various
satellites components including the controllers, in this paper, we
present a 3D simulator and the investigation of a SDRE control law
performance by simulations. The simulator is implemented based on
Java and related open-source software libraries (Hipparchus -
linear algebra library, and Orekit - flight dynamics library),
therefore, it can run in a variety of platforms and it has low
cost. These open-source libraries were extended in order to solve
the optimization problem that is the cornerstone of the SDRE
method, a major contribution of the simulator. The simulator is
evaluated taking into account a typical mission of the Brazilian
National Institute for Space Research (INPE), in which the SCS
must stabilize a satellite in three-axis using reaction wheels so
that the optical payload can point to the desired target. Two SCS
control laws (a linear and a SDRE based) were simulated for an
attitude maneuver in the launch and early orbit phase (LEOP), the
upside-down maneuver. The results of simulations shown that
SDRE-based controller provides better performance.",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and
{Universidade Federal do ABC (UFABC)}",
doi = "10.1007/978-3-319-99268-6_38",
url = "http://dx.doi.org/10.1007/978-3-319-99268-6_38",
language = "en",
targetfile = "romero_satelllite.pdf",
urlaccessdate = "03 jun. 2024"
}