| 摘要 |
The system (200) has a magnetometer sensor (202) and a cosine sun sensor (204) provided to predict direction of terrestrial magnetic field and satellite-sun in a local orbital reference frame. An attitude estimator (208) is coupled to the sensors to determine attitude of satellite in relation to the frame, angle between the sun direction and satellite axis, and a position on orbit of the satellite. A boost generation module is coupled to the estimator to generate signals to activate thrusters of the satellite when the attitude, angle and position values are equal to predefined values. Independent claims are also included for the following: (1) a method for deorbiting a satellite (2) a computer program product comprising a set of code instructions for performing a method for deorbiting a satellite. |
