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Singular value decomposition-based coordination control method of single gimbal control moment gyros (SGCMGs)

A technology for controlling moment gyro and singular value decomposition, applied in attitude control and other directions, can solve the problems that cannot guarantee the complete avoidance of SGCMGs singularity and the accurate output of torque, and achieve the effect of avoiding premature saturation

Active Publication Date: 2012-07-11
BEIHANG UNIV
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Problems solved by technology

The biggest problem with this solution is that when only the SGCMGs in the core cabin are used to control the assembly, if some gyros fail, the existing control laws cannot guarantee that the SGCMGs can simultaneously achieve singular complete avoidance and precise torque output

Method used

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  • Singular value decomposition-based coordination control method of single gimbal control moment gyros (SGCMGs)
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  • Singular value decomposition-based coordination control method of single gimbal control moment gyros (SGCMGs)

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Embodiment Construction

[0024] The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0025] In order to introduce the present embodiment more clearly, the principle of the output torque of the SGCMG is briefly explained first, and then the implementation of the method is explained in combination with two sets of SGCMGs with a pentagonal pyramid configuration. It should be emphasized that this method only requires two sets of SGCMGs in the pentagonal pyramid configuration, and does not depend on the specific installation method.

[0026] see figure 1 , the SGCMG consists of a rotor rotating at a constant speed and a frame supporting the rotor, is the direction of the rotor spin axis, is the rotational speed direction of the frame shaft, Opposite to the output control torque direction. The rotor spin axis is installed orthogonally to the frame axis, and is driven by the rotor motor and the frame motor respectively. Th...

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Abstract

The invention relates to a singular value decomposition-based coordination control method of single gimbal control moment gyros (SGCMGs). The singular value decomposition-based coordination control method comprises the following steps of: distributing instruction moment required for controlling an entire spacecraft to two sets of SGCMGs according to a certain proportion; decomposing the instruction moment distributed to the set A of SGCMGs again by using a singular value decomposition method; distributing an instruction moment component in the singular direction of the set A of SGCMGs to the set B of SGCMGs; still distributing an instruction moment component perpendicular to the singular direction of the set A of SGCMGs to the set A of SGCMGs; after distribution, solving instruction gimbal angular velocities of the two sets of SGCMGs respectively; operating according to the respective instruction gimbal angular velocity; and acting the sum of output moment on the spacecraft to finish accurate attitude control. According to the singular value decomposition-based coordination control method, the gyros can still accurately and effectively output control moment to control the attitudeof the spacecraft while a part of gyros fails and the gyros are singular and the probability of premature saturation of a single set of SGCMGs is also avoided to the greatest extent without configuring an extra execution mechanism.

Description

technical field [0001] The invention relates to an attitude control method of a spacecraft, in particular to a control method of a single-frame control moment gyro group. Background technique [0002] With the development of the aerospace industry, modern spacecraft have higher and higher requirements for the accuracy, life and reliability of the attitude control system. The spacecraft on-orbit attitude control is mainly realized through the output control torque of the actuator. [0003] At present, the attitude control actuators used by spacecraft mainly include jet thrusters, angular momentum exchange devices, and magnetic torquers. Among them, the angular momentum exchange device has the advantages of being able to provide continuous attitude control torque, not consuming fuel, not polluting the optical equipment and flight environment, and not easy to excite the vibration of the spacecraft's flexible accessories, so it is widely used as the main actuator of the spacecr...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 金磊桂海潮徐世杰
Owner BEIHANG UNIV
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