Steering law singularity avoidant spacecraft attitude control system

An attitude control and attitude controller technology, applied in the field of spacecraft attitude control system, can solve the problems of unable to generate frame angular rate, unable to meet high precision requirements of high agility spacecraft attitude control, frame deadlock and so on

Active Publication Date: 2009-01-28
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

That is to say, this algorithm sacrifices the output accuracy of the control torque gyro group torque in exchange for singularity avoidance, and this steering law algorithm cannot produce the frame angular rate required for non-zero torque along the singular direct

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  • Steering law singularity avoidant spacecraft attitude control system
  • Steering law singularity avoidant spacecraft attitude control system
  • Steering law singularity avoidant spacecraft attitude control system

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Embodiment Construction

[0030] Such as figure 1 , 2 As shown, the attitude control system of the present invention is composed of an attitude controller 1, an attitude measurement unit 2, a gyro group maneuvering law unit 3, a control moment gyro group 4, an attitude task management unit 5, a frame angular position measurement unit 6 and a spacecraft 7. The gyro group steering law unit 3 further includes a control moment gyro angular momentum table 10 , a zero motion algorithm module 12 and a pseudo-inverse steering law algorithm module 11 .

[0031] The attitude measurement unit 2 monitors the attitude information of the spacecraft 7 in real time and sends them to the attitude controller 1, the gyro group maneuvering law unit 3 and the attitude task management unit 5 respectively; the frame angle position measurement unit 6 monitors and controls the frame angle of the moment gyro group 4 in real time. The position is sent to the attitude controller 1; the attitude controller 1 determines the torque...

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Abstract

The invention relates to a steering-law singularity avoiding aircraft attitude control system, comprising an attitude task managing unit, an attitude controller, an attitude measuring unit, a gyro group steering-law unit, a frame angle position measuring unit, a control moment gyro group and an aircraft. The gyro group steering-law unit calculates the frame angle rate of the control moment gyro group by cooperating control moment gyro angle momentum table, zero motion algorithm and pseudoinverse steering-law algorithm, and adopts the angle rate value as the set signal of the control moment gyro group to improve the control precision of the aircraft attitude. The steering-law singularity avoiding aircraft attitude control system introduces the steering-law design method that chooses frame angle rate and the initial value of frame angle position based on look-up table, realizes accurate moment output of the control moment gyro group, avoids the singularity problem produced in the process of calculating frame angle rate of the control moment gyro group by the pseudoinverse steering-law algorithm as well as avoids the deadlock problem caused by the control moment gyro steering law when adopting zero motion algorithm and robust pseudoinverse steering-law iterative computations.

Description

technical field [0001] The invention relates to a spacecraft attitude control system, in particular to a spacecraft attitude control system capable of judging whether the control moment gyroscope enters a singularity zone and avoiding the singularity. Background technique [0002] The actuators of the spacecraft attitude control system mainly include three categories: (1) thrusters; (2) flywheel actuators: including reaction wheels, (bias) momentum moment wheels, frame momentum moment wheels, and control moment gyroscopes; (3) ) Environmental torque actuator. The control moment gyroscope has become a key actuator necessary for attitude control of large spacecraft such as space stations because of its ability to output large torque. The single-frame control moment gyroscope is also the best choice for high-agility small satellite attitude actuators because of its torque amplification and good dynamic performance. [0003] The single-frame control moment gyroscope is compose...

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Application Information

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IPC IPC(8): B64G1/24
Inventor 于灵慧刘胜利王文松
Owner AEROSPACE DONGFANGHONG SATELLITE
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