@InProceedings{RomeroSouz:2019:ApNeOp,
author = "Romero, Alessandro Gerling and Souza, Luiz Carlos Gadelha de",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and
{Universidade Federal do ABC (UFABC)}",
title = "Application of a new optimal factorization of the SDRE method in
the satellite attitude and orbit control system design with
nonlinear dynamics",
booktitle = "Proceedings...",
year = "2019",
pages = "27--33",
organization = "Internaitonal Conference on Advances in Satellite and Space
Communications, 11.",
publisher = "IARA",
keywords = "nonlinear control, SDRE method, satellite control.",
abstract = "The satellite Attitude and Orbit Control System (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.
Therefore, in such cases, it is expected that nonlinear control
techniques yield better performance than the linear control
techniques. One candidate technique for the design of AOCS control
law under a large maneuver is the State-Dependent Riccati Equation
(SDRE). SDRE entails factorization (that is, parameterization) of
the nonlinear dynamics into the state vector and the product of a
matrix-valued function that depends on the state itself. In doing
so, SDRE brings the nonlinear system to a (not unique) linear
structure having State-Dependent Coefficient (SDC) matrices and
then it minimizes a nonlinear performance index having a
quadratic-like structure. The non uniqueness of the SDC matrices
creates extra degrees of freedom, which can be used to enhance
controller performance; however, it poses challenges since not all
SDC matrices fulfill the SDRE requirements. Moreover, regarding
the satellite's kinematics, there is a plethora of options, e.g.,
Euler angles, Gibbs vector, Modified Rodrigues Parameters (MRPs),
quaternions, etc. Once again, some kinematics formulations of the
AOCS do not fulfill the SDRE requirements. In this paper, we
evaluate the factorization options of SDC matrices for the AOCS
exploring the requirements of the SDRE technique. Considering a
Brazilian National Institute for Space Research (INPE) typical
mission, in which the AOCS must stabilize a satellite in
threeaxis, the application of the SDRE technique equipped with the
optimal SDC matrices can yield gains in the missions. The initial
results show that MRPs for kinematics provides an optimal SDC
matrix.",
conference-location = "Valencia, Spain",
conference-year = "24-28 mar.",
language = "en",
targetfile = "spacomm_2019_3_10_20010.pdf",
urlaccessdate = "28 mar. 2024"
}