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Spacecraft attitude control method for controlling moment gyro singularity avoidance

A technology for controlling moment gyro and singularity avoidance, applied in attitude control, three-dimensional position/channel control and other directions, which can solve the problem of singularity of SGCMG group

Active Publication Date: 2016-01-06
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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  • Spacecraft attitude control method for controlling moment gyro singularity avoidance
  • Spacecraft attitude control method for controlling moment gyro singularity avoidance
  • Spacecraft attitude control method for controlling moment gyro singularity avoidance

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Embodiment Construction

[0037] 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 .

[0038] A spacecraft attitude control method for controlling moment gyroscope singularity avoidance, the specific steps are:

[0039] The first step is to determine the SGCMG group angular momentum set

[0040] 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:

[0041] (1)

[0042] in is the number of ...

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Abstract

The invention discloses a spacecraft attitude control method for controlling moment gyro singularity avoidance, specifically comprising the steps as follows: S1, solving an SGCMG (single gimbal control moment gyro) group angular momentum set; S2, deciding the angular momentum amplitude of an SGCMG group and spacecraft system; S3, determining the optimal control performance index of a spacecraft attitude control system; S4, determining a linear model of the SGCMG group and spacecraft system; S5, determining the linearization range of the SGCMG group and spacecraft system; S6, determining the linearization range meeting the constraints; and S7, using nonlinear predictive control to implement spacecraft attitude control. By using the method, the attitude of a spacecraft can be controlled precisely, the spacecraft launching cost is reduced, and the in-orbit operation life of spacecrafts is increased.

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 torque 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...

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
Inventor 张佳为许诺张丽华
Owner BEIJING MECHANICAL EQUIP INST
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