Spin-axis pointing of a magnetically actuated spacecraft

Spacecraft Attitude Control Using Magnetic and Mechanical Actuation

“…In the latter case, the kinematics of Euler angles in Eqs. (8), (9), and (10) is conveniently rearranged as follows:ψ = (−ω 1 sin θ + ω 3 cos θ + n sin φ cos ψ) / cos φ…”

“…where all the vector quantities, including H d , are expressed in terms of body frame components [9].…”

“…In a recent paper [9], three of the authors of the present work proposed a control law that leads a spacecraft to acquire a desired pure spin condition around one of the principal axes of inertia by means of magnetic actuators only, while aiming the spin axis toward a prescribed direction in the inertial space. A similar approach is used in this framework, where the error dynamics equation is rst derived for two error signals, namely the angular momentum error in the body frame and the angular momentum error with respect to the desired direction of the wheel spin axis in the inertial frame.…”

“…The error dynamics is then recast in the classical form of a nominal system perturbed by a vanishing perturbation term. After proving global exponential stability for the nominal system controlled by MTs, the result discussed in [9] is here extended to the perturbed one. As a further contribution, full three-axis attitude stabilization is obtained (rather than simple spin-axis pointing) by means of a proper choice of the wheel control law governing the pitch angle dynamics.…”

Geomagnetic field models for satellite angular motion

“…Common schemes of one axis attitude control of spin stabilized satellites were proposed in [21,22]. Remarkable examples of analysis or implementation can be found in [2,13,[23][24][25][26][27][28][29]. Spin stabilization allows promising optimal reorientation problems statements [30][31][32].…”