In this paper, a method for nano-satellite attitude and control during the transition mode is developed. The performance and stability of the control law is analyzed and temporal results are verified using simulation. This AOCS mode is used after detumbling mode and before mission mode. The satellite studied is a triple cubesat (10cm×10cm×30cm) on a polar orbit with an altitude around 800km. A three-axes-magnetometer is used as sensor and one magneto-torquer per axis as actuators. This all magnetic configuration is suitable to use for small satellites that request low cost, low weight and reliable equipment for the altitude considered. Moreover a reaction wheel is used to enhance the satellite stability in the orbit plan. The law developed here does not need estimator and the accuracy and the stability reached could be compliant with mission mode for some nano-satellites missions that do not need very strict performances such as communications and telemetry.
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