SATELLITE CONSTELLATION DESIGN FOR MULTI-TARGET REMOTE SENSING MISSION

For the mission of achieving a maximum revisit interval of less than 1 hour for multi-target within a given area on the ground with as few satellites as possible, and try to ensure that the revisits are evenly distributed, the first satellite orbit is designed using the two-body model. The satellite can achieve two observations of the same target point within one day, and then the mission satellite constellation is designed. To calculate the perturbation of the satellite, J(2) perturbations must be considered in a time scale of one week. The influence of J(2) perturbation on the satellites for this mission is mainly reflected in the change of orbit's right ascension of ascending node (RAAN). Calculate the influence of J(2) perturbation on the RAAN and guide the amendment of the semi-major axis of the orbit to realize that the satellite can observe the same target point twice a day and then design the constellation to accomplish the mission.