Analysis of analytical attitude propagators for spin-stabilized satellites
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Analysis of analytical attitude propagators for spin-stabilized satellites M. C. Zanardi1 · C. C. Celestino1 · G. Borderes Motta2 · E. M. França1 · R. V. Garcia3
Received: 1 April 2017 / Revised: 15 November 2017 / Accepted: 10 May 2018 © SBMAC - Sociedade Brasileira de Matemática Aplicada e Computacional 2018
Abstract In this paper, analytical attitude propagators for spin-stabilized satellites are analyzed. For this purpose, external torques are introduced in the motion equations such as solar radiation pressure torque, aerodynamic torque, gravity gradient torque, and magnetic residual and eddy current torques. For the magnetic torques, it used both the dipole and quadripole Earth’s magnetic field models. The obtained analytical solution is applied and compared with actual data for Brazilian data collection satellites SCD1 and SCD2. The results, when a daily data update is applied, based on the INPE-Brazilian Institute for Space Research supplied data, show a good agreement of all involved parameters with the actual deviations in the parameter values within the precision required for the satellite mission. This permits to conclude that the used theory is suitable for the studied problem. Thus, the propagators presented in this work can be applied to predict the rotational motion of spin-stabilized artificial satellites, particularly for SCD1 and SCD2 satellites over the considered time period. Keywords Analytical propagators · Spin-stabilized satellites · Environmental torques Mathematics Subject Classification 34A34
Communicated by Elbert Macau, Antônio Fernando Bertachini de Almeida Prado and Othon Cabo Winter.
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M. C. Zanardi [email protected]
1
Federal University of ABC, Av. Dos Estados, 5001, Bangu, CEP 09210-580 Santo André, SP, Brazil
2
São Paulo State University, Av. Dr. Ariberto Pereia da Cunha., 333, CEP 12.516-410 Guaratinguetá, SP, Brazil
3
USP (University of São Paulo), EEL, Estrada Municipal do Campinho, s/n., CEP 12602-810 Lorena, SP, Brazil
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1 Introduction The attitude of a satellite is the representation of its spatial orientation with respect to a reference system. The knowledge of satellite positioning is necessary for a great number of applications such as: data transmission, remote sensing systems, and climatic monitoring, since the reception and transmission antennas of these satellites must be constantly pointed to Earth. However, once in space, these satellites are exposed to many perturbations and for keeping their mission required attitude some corrections must be applied. There are many onboard devices that can actively perform attitude corrections, for example, the reaction wheels and the gas jets. A passive method that can be used to decrease the number of correction maneuvers is the so called spin stabilization. In this method, the rotation axis is aligned with the axis with the greater inertia principal moment of the satellite. The theory developed in this paper is applied for this kind of satellite. Studies related to the dynamic of sa
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