%0 Conference Proceedings
%4 sid.inpe.br/plutao/2018/12.14.19.53.21
%2 sid.inpe.br/plutao/2018/12.14.19.53.22
%@doi 10.2514/6.2018-2536
%@isbn 9781624105623
%F lattes: 5964335207790589 3 RomeroSouzChag:2018:ApSDTe
%T Application of the SDRE technique in the satellite attitude and orbit control system with nonlinear dynamics
%D 2018
%A Romero, Alessandro Gerlinger,
%A Souza, Luiz Carlos Gadelha de,
%A Chagas, Ronan Arraes Jardim,
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@electronicmailaddress
%@electronicmailaddress lcgadelha@gmail.com
%@electronicmailaddress ronan.arraes@inpe.br
%B International Conference on Space Operations, 15 (SpaceOps)
%C Marseille, France
%8 28 may - 01 june
%I American Institute of Aeronautics and Astronautics
%S Proceedings
%X 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).
%@language en
%3 romero_application.pdf
%U http://www.spaceops2018.org