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The paper presents some aspects for synthesis of small satellites attitude control. The satellite nonlinear model presented here will be with six degrees of freedom. After movement equation linearization the stability and command matrixes will be established and the controller will be obtained using gradient and gradient method. Two attitude control cases will be analysed: the reaction wheels and the micro thrusters. The results will be used in the project European Space Moon Orbit - ESMO founded by European Space Agency in which the University POLITEHNICA of Bucharest is involved.

Attitude Control Synthesis for Small Satellites Using Gradient Method. Part I - Nonlinear Equations