The invention relates to a multi-stage attitude control method for a remote sensing micro-nano satellite, and belongs to the technical field of spacecraft attitude control. A three-axis magnetic moment device and a momentum wheel set are adopted as an attitude control execution component, and the attitude control method for the four main stages of recemization after satellite-rocket separation, counterglow capture, counterglow orientation and counter-earth remote sensing is designed, and an attitude mobile control method for the two stages of counterglow orientation and counter-earth remote sensing is designed. According to the recemization stage, the large angular rate of the satellite obtained after satellite-rocket separation is eliminated, and the basic controlled attitude is built; inthe counterglow capture and counterglow orientation stages, it is ensured that a sun sailboard is in the charging state for a long time; in the counter-earth remote sensing stage, it is ensured thatthe remote sensing photographing task is completed. According to the method, traditional PD control is adopted as the foundation, on the basis of feedforward control, quaternion is used for representing attitude errors, the method has the advantages of being rapid in satellite maneuvering response, high in steady state robustness and high in control precision, and the task requirement for a remotesensing micro-nano satellite is met.