Constant-value disturbance torque compensation method and system for oblique-flying and large-inertia coupling satellite

Abstract

The invention discloses a constant-value disturbance torque compensation method for oblique-flying and large-inertia coupling satellite. The compensation method comprises steps as follows: a satellite attitude dynamical equation is simplified in a steady state; X-axis gyroscopic torque and Z-axis gyroscopic torque are obtained according to a dynamical coupling relation of an X axis and a Z axis; offset angular momentum of the X axis and offset angular momentum of the Z axis are obtained according to the relation between the X-axis and Z-axis gyroscopic torque and constant-value disturbance torque; magnetic torquer unloading is performed according to the obtained offset angular momentum, and angular momentum offset is realized. With the adoption of the method for producing gyroscopic torque compensation through angular momentum offset, angular momentum offset is realized easily through magnetic dumping, management of the angular momentum of the system is controlled by compensating the constant-value disturbance torque, saturation of the angular momentum of the satellite can be avoided under the condition that the magnetic torquer is fixed, the problem of high probability of saturation of the angular momentum due to the constant-value disturbance torque in an angular momentum exchange attitude control system is solved, and the beneficial effect that the angular momentum offset is applied to magnetic dumping of satellite attitude control is realized.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a method and system for compensating a constant disturbance moment of an obliquely flying large-inertia coupling satellite. Background technique [0002] Under the action of external disturbance torque, the X and Z axes will slowly accumulate the angular momentum of the flywheel due to the existence of periodic external disturbance torque, and finally reach saturation, while the Y channel, due to the constant disturbance torque, has a single angular momentum The edge accumulation will also reach saturation. In order not to make the flywheel work in a saturated state, external torque must be used to absorb the excess angular momentum, while meeting the system control accuracy and stability index requirements. The high-precision satellite control system generally uses the magnetic torque generated by the magnetic torque device to interact with the earth's magneti...

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Problems solved by technology

Therefore, a large unloading torque will be required, and even angular momentum saturation will occur, which is not conducive to the normal operation of the angular momentum exchange attitude control system.

[0004] At present, there is no description or report of the similar technology of the present invention, and no similar data at home and abroad have been collected yet.

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