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Attitude control information joint estimation method under satellite attitude angle deviation

A technology of satellite attitude and angle deviation, applied in the field of joint estimation of attitude control information under small angle deviation of satellite attitude, can solve the problem of low control accuracy, achieve the effect of improving determination accuracy, simple method, and convenient on-orbit implementation

Inactive Publication Date: 2018-01-23
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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Problems solved by technology

[0004] In order to solve the problem of low control accuracy caused by the difficulty of accurately estimating the attitude control information under small attitude angle deviations during the satellite attitude maneuvering process, the present invention provides a method for jointly estimating attitude control information under small attitude angle deviations of satellite attitudes

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  • Attitude control information joint estimation method under satellite attitude angle deviation
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  • Attitude control information joint estimation method under satellite attitude angle deviation

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specific Embodiment approach 1

[0034] Specific implementation mode 1. Combination Figure 1 to Figure 19 Describe this embodiment, the attitude control information joint estimation method under the satellite attitude angle deviation, based on the measurement information of the spaceborne sensor and the actuator, using the satellite attitude dynamics, kinematics and reaction flywheel dynamics model, the attitude error is realized through iterative calculation The joint accurate estimation of the six variables, quaternion, attitude error angular velocity, reaction flywheel angular momentum, reaction flywheel friction torque, external disturbance torque, and constant drift of the fiber optic gyroscope, provides accurate input for the attitude control algorithm. specifically:

[0035] Step A. Collect the current measurement values ​​of the star sensor, fiber optic gyroscope, reaction flywheel and GPS through the satellite-borne central computer, and obtain the satellite attitude measurement quaternion q at the ...

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Abstract

The invention discloses an attitude control information joint estimation method under the satellite attitude angle deviation, and relates to the technical field of satellite attitude determination andcontrol. The problem that in the satellite attitude maneuvering process, attitude control information under the attitude small angle deviation is difficult to estimate precisely, so that the controlprecision is low is solved. The method comprises the steps that on the basis of measurement information of a spaceborne sensor and an actuating mechanism, under the attitude small angle deviation, joint precision estimation of variables such as the satellite attitude error quaternion, satellite attitude error angular velocity, reaction flywheel angular momentum, reaction flywheel friction moment,external disturbance moment and fiber-optic gyroscope constant drift is achieved in a loop iteration mode by means of satellite attitude dynamics, kinematics and a reaction flywheel dynamical model, and precise attitude control information is provided for high-precision satellite attitude control. The method is achieved through a software algorithm, and the method is simple and easy to implement.

Description

technical field [0001] The invention relates to the technical field of satellite attitude determination and control, in particular to a method for joint estimation of attitude control information under small angle deviation of satellite attitude. Background technique [0002] The high-precision control of satellite attitude depends on the sensors and actuators used, attitude determination algorithm and attitude control algorithm. When the hardware configuration is determined, the control performance is mainly improved through software. The attitude determination algorithm mainly calculates the attitude control information required by the satellite attitude control algorithm. The amount and accuracy of the information have a great influence on the overall control performance of the satellite attitude, especially after the satellite attitude completes the large-angle maneuver, it will move towards the target attitude. During the approaching process, it affects the convergence...

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Application Information

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IPC IPC(8): B64G1/24
Inventor 范国伟常琳徐伟王绍举杨秀彬王旻
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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