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A Spacecraft Attitude Control Method for Controlling Moment Gyro Singularity Avoidance

A technology for controlling moment gyroscopes and singularity avoidance, applied in attitude control, three-dimensional position/course control, etc., can solve problems such as SGCMG group singularities, achieve the effect of reducing launch costs and improving the life of on-orbit operations

Active Publication Date: 2018-04-13
BEIJING MECHANICAL EQUIP INST
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Problems solved by technology

[0003] The object of the present invention is to provide a kind of spacecraft attitude control method for controlling moment gyroscope singularity avoidance, solve the singularity problem that SGCMG group exists in the past control method

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  • A Spacecraft Attitude Control Method for Controlling Moment Gyro Singularity Avoidance
  • A Spacecraft Attitude Control Method for Controlling Moment Gyro Singularity Avoidance
  • A Spacecraft Attitude Control Method for Controlling Moment Gyro Singularity Avoidance

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Embodiment Construction

[0038] Moment of inertia of rigid body spacecraft , the initial quaternion of the spacecraft , the instruction quaternion , the initial angular velocity , command angular velocity , , the external disturbance torque along the maximum magnitude is . The SGCMG group adopts a pyramid configuration, Mounting Angle for SGCMG Frame, Flywheel Angular Momentum , the initial and terminal frame angular velocities , the maximum frame angular velocity , the maximum frame angular acceleration .

[0039] A spacecraft attitude control method for controlling moment gyroscope singularity avoidance, the specific steps are:

[0040] The first step is to determine the SGCMG group angular momentum set

[0041] According to the singular angular momentum of the SGCMG group Draw the singular momentum surface of the redundant configuration of the SGCMG group. The expression of the singular angular momentum of the SGCMG group is:

[0042] (1)

[0043] in is the number o...

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Abstract

The invention discloses a spacecraft attitude control method for controlling moment gyroscope singularity avoidance. The specific steps are as follows: the first step is to obtain the angular momentum set of the SGCMG group; Determine the momentum amplitude; the third step is to determine the optimal control performance index of the spacecraft attitude control system; the fourth step is to determine the linearization model of the overall system of the SGCMG group and the spacecraft; the fifth step is to determine the overall system composed of the SGCMG group and the spacecraft The linearization range of the system; the sixth step is to determine the linearization range that meets the constraints; the seventh step is to use nonlinear predictive control to realize spacecraft attitude control. The invention completes the precise control of the attitude of the spacecraft, and achieves the purposes of reducing the launch cost of the spacecraft and improving the service life of the spacecraft on orbit.

Description

technical field [0001] The invention relates to a spacecraft attitude control method, in particular to a spacecraft attitude control method for controlling moment gyroscope singularity avoidance. Background technique [0002] Single gimbal control moment gyro (single gimbal control moment gyro, SGCMG) group, as the actuator of spacecraft attitude control system, has the advantages of large moment magnification, simple physical structure, long service life, etc., and is widely used in the field of spacecraft attitude control. However, there are geometric singularity problems that are difficult to solve in the application process of SGCMG group. At present, spacecraft attitude control and SGCMG group control are usually considered separately at home and abroad. The spacecraft attitude control part only uses the spacecraft angular velocity and spacecraft attitude as the feedback variables of the system state, so that the designed feedback controller realizes the system state S...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
Inventor 张佳为许诺张丽华
Owner BEIJING MECHANICAL EQUIP INST
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