Angular momentum control method of spacecraft in inertial system

Abstract

The invention discloses angular momentum control method of a spacecraft in an inertial system. The method is characterized in that a three-axis stabile control is performed in the inertial system, and the feedback design is performed based on the angular momentum and three-axis posture angle information of a performing mechanism to obtain a feedback controller. According to the method, that the gravity gradient torque is to be more than the pneumatic torque is removed; the performing mechanism is unsaturated while the long-term stable flying is ensured; the method is applied to the spacecraft posture control in the circumstance that a magnetorquer cannot be assembled or the magnetorquer suffers from fault and unloading cannot be or is not proposed to be performed by the air injection mode.

Description

technical field [0001] The invention relates to an angular momentum control method, which belongs to the field of spacecraft attitude control. Background technique [0002] When a spacecraft using angular momentum exchange actuators (flywheel, control torque gyroscope) for attitude control is in orbit for a long time, under the action of space environment disturbance torque, the angular momentum of the actuator will increase, and then it will reach saturation, so it is necessary to carry out angular momentum. Momentum unloading. At present, the main unloading methods include magnetic torquer unloading and jet unloading. [0003] Due to the large inertia of the space station, the environmental moment it is subjected to is also large. For example, the maximum aerodynamic moment of the International Space Station reaches 8.8Nm. The accumulation of angular kinetics caused by such a large external disturbance torque cannot be unloaded by a magnetic torque device. Therefore, the ...

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