@InProceedings{RomeroSouzChag:2018:ApSDTe,
author = "Romero, Alessandro Gerlinger and Souza, Luiz Carlos Gadelha de and
Chagas, Ronan Arraes Jardim",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto
Nacional de Pesquisas Espaciais (INPE)} and {Instituto Nacional de
Pesquisas Espaciais (INPE)}",
title = "Application of the SDRE technique in the satellite attitude and
orbit control system with nonlinear dynamics",
booktitle = "Proceedings...",
year = "2018",
organization = "International Conference on Space Operations, 15. (SpaceOps)",
publisher = "American Institute of Aeronautics and Astronautics",
abstract = "The satellite attitude and orbit control subsystem (AOCS) can be
designed with success by linear control theory if the satellite
has slow angular motions and small attitude maneuver. However, for
large and fast maneuvers, the linearized models are not able to
represent all the perturbations due to the effects of the
nonlinear terms present in the dynamics and in the actuators
(e.g., saturation) which can damage the systems performance.
Therefore, in such cases, it is expected that nonlinear control
techniques yield better performance than the linear control
techniques, improving the AOCS pointing accuracy without requiring
a new set of sensors and actuators. One candidate technique for
the design of AOCS control law under a large and fast maneuver 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. The
Brazilian National Institute for Space Research (INPE, in
Portuguese) was demanded by the Brazilian government to build
remote-sensing satellites, such as the Amazonia-1 mission. In such
missions, the AOCS must stabilize the satellite in three-axes so
that the optical payload can point to the desired target.
Currently, the control laws of AOCS are designed and analyzed
using linear control techniques in commercial software. In this
paper, we discuss whether the application of the SDRE technique in
the AOCS design can yield gains in the missions developed by INPE.
Moreover, we report a proof of concept of an open-source satellite
simulator built to analyze control laws based on SDRE. This
satellite simulator is implemented in Java using Hipparchus
(linear algebra library; which was extended in order to support
the SDRE technique) and Orekit (flight dynamics framework).",
conference-location = "Marseille, France",
conference-year = "28 may - 01 june",
doi = "10.2514/6.2018-2536",
url = "http://dx.doi.org/10.2514/6.2018-2536",
isbn = "9781624105623",
label = "lattes: 5964335207790589 3 RomeroSouzChag:2018:ApSDTe",
language = "en",
targetfile = "romero_application.pdf",
url = "http://www.spaceops2018.org",
urlaccessdate = "20 abr. 2024"
}