Orbit control method for carrying out interference angular momentum self-balancing by utilizing attitude rotation

Abstract

The invention discloses an orbit control method for carrying out interference angular momentum self-balancing by utilizing attitude rotation, and belongs to the technical field of spacecraft orbit control. The method comprises the following steps: step 1, establishing a satellite orbit control task attitude and keeping the satellite orbit control task attitude stable; step 2, performing attitude rotation around a thrust vector axis; and step 3, enabling the thruster to work to carry out orbit control. For a satellite which is not provided with an attitude control thruster or is damaged by theattitude control thruster, in a satellite orbit control task, the attitude of the satellite is enabled to rotate around the vector axis of the thruster, and the angular momentum of each axis of the satellite can be always controlled within a certain range under the condition that the propulsion disturbance torque of the satellite is continuously acted. Therefore, the orbit control task can be continuously implemented for a long time under the condition that the satellite only has the orbit control thruster, and the orbit control capability of the satellite is greatly improved.

Description

technical field [0001] The invention relates to an orbit control method using attitude rotation to self-balance disturbance angular momentum, and belongs to the technical field of spacecraft orbit control. Background technique [0002] In the satellite orbit control mission, due to the existence of thruster installation error, the orbit control thruster will generate disturbance torque when it is working. For satellites without attitude control thrusters or with damaged attitude control thrusters, the disturbance angular momentum generated by the accumulation of orbit control disturbance moments can only be absorbed by the satellite's angular momentum management devices, such as flywheels and control moment gyroscopes. Due to the limited angular momentum that can be absorbed by the angular momentum management device of the satellite, the cumulative angular momentum generated by the propulsion disturbance torque will cause the saturation of the angular momentum of the entire ...

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Problems solved by technology

[0004] The purpose of the present invention is to propose an orbit control method that utilizes attitude rotation to disturb the angular momentum self-balancing, utilizes the principle of the periodic exchange of angular momentum of the remaining two axes during the rotation of the satellite around the thrust direction, and converts the entire star angle in the orbit control task The momentum is controlled within a certain range, so as to solve the problem that the continuous long-term orbit control mission will cause the angular momentum saturation of the whole star and affect the orbit control ability of the satellite

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