Abstract
A feasibility study is presented for using micro Pulsed Plasma Thrusters (μPPT) on a 3U CubeSat to perform attitude control to meet pointing requirements at altitudes between 400 and 1000 km. The orbits and attitude control are consistent with science missions for ionospheric and solar observations. The positioning of the thrusters is such that they provide full, three-axis rotational control while maximizing the efficiency of each pulse. The aerodynamic, magnetic, solar radiation, and gravity gradient disturbance torques are included in the formulation. Sensor modeling is also included. The study involves realistic power constraints anticipated on the 3U CubeSat. The paper presents the overall design of the 3U CubeSat and focuses on the attitude determination and control (ADC) approach and implementation. The paper also introduces the control strategy and numerical simulation results for stabilization, pointing and spinning applications.
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