Attitude Determination and Prediction of Spin-Stabilized Satellites

Thomas, Lia; Cappellari, James O.

doi:10.1002/j.1538-7305.1964.tb04104.x

Cited by 11 publications

(3 citation statements)

References 9 publications

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“…where I z is the moment of inertia along the spin axis, N x , N y , N z are the components of the external torques in the body system and here are given by the sum of the mean components of gravity gradient, aerodynamic, solar radiation, residual magnetic and eddy current torques. The analytical approach for this case is similar to that of Thomas and Cappelare (1964) and Yu (1963). Applications in these references were done for the Telstar satellites using the magnetics torque with dipolo model for the geomagnetic field.…”

Section: Analytical Approachmentioning

confidence: 91%

Numerical and analytical approach for the spin-stabilized satellite attitude propagation

et al. 2016

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This paper presents the comparison between the numerical and analytical results of a spacecraft attitude propagation for a spin-stabilized satellite. Some external torques are introduced in the equations of the motion and the comparisons are done considering that these torques are acting together, which are: gravity gradient, aerodynamic, solar radiation, magnetic residual and eddy current. In the numerical approach it is used the quaternion to represent the attitude. This numerical approach can be applied for any kind of satellite. The analytical approach is applied directly for a spin-stabilized satellite and the equations of motion are described in terms of the spin velocity, spin axis right ascension and declination angles. An analytical solution of these equations is presented and valid for one orbit period. Applications are developed considering the Brazilian spin-stabilized satellites SCD1 and SCD2. The comparisons are important to validate some simplifications that are required in

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Section: Analytical Approachmentioning

confidence: 91%

Numerical and analytical approach for the spin-stabilized satellite attitude propagation

et al. 2016

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“…These components are obtained in terms of the geocentric inertial components of the geomagnetic field (Thomas and Cappelari, 1964) and the attitude quaternion of the satellite . In order to describe the geomagnetic field, the dipole vector model (Thomas and Cappelari ,1964;Zanardi et al, 2005) is used.…”

Section: Magnetic Torquesmentioning

confidence: 99%

“…The geomagnetic field is described by the dipole vector model (Thomas and Cappelari ,1964;Zanardi et al, 2005).…”

Section: Torque Due Lorentz Forcementioning

confidence: 99%