On-orbit refueling spacecraft attitude control method

An attitude control and spacecraft technology, which is applied in attitude control, non-electric variable control, control/regulation systems, etc., can solve problems such as difficulty in ensuring the effectiveness of control methods and control accuracy, and difficulty in modeling the moment of inertia of the system.

Active Publication Date: 2016-09-21
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

However, in actual engineering, it is often necessary to adjust the attitude of the spacecraft at a large angle. At the same time, it is difficult to accurately m

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  • On-orbit refueling spacecraft attitude control method
  • On-orbit refueling spacecraft attitude control method

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Embodiment Construction

[0142] The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention.

[0143] The attitude control method of the on-orbit refueling spacecraft provided by the present invention is described below in conjunction with specific examples:

[0144] Step 1: Given the target attitude matrix C d and target angular velocity ω d

[0145] The given target pose matrix is The target angular velocity is ω d =[0,0,0] T .

[0146] Step 2: Calculate the amount of error

[0147] Calculate the attitude error matrix between the target attitude matrix and the actual attitude matrix: Among them, C is the actual attitude matrix; calculate the error angular velocity between the target angular velocity and the actual angular velocity: Amon...

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Abstract

The invention provides an on-orbit refueling spacecraft attitude control method, and the method comprises the steps: firstly calculating an error amount through a given target attitude and actual attitude; secondly calculating an auxiliary variable and a selection reaching law, introducing an inertia self-adaption law and a control gain self-adaption law, and building a self-adaption sliding mode attitude control law; thirdly taking an absolute value of a sliding mode and a first-order differential thereof as the input of a fuzzy adjuster so as to effectively inhibit the vibration of sliding mode control, taking the thickness of a sliding mode boundary layer as the output of the fuzzy adjuster, building a self-adaption sliding mode attitude control law with a fuzzy boundary layer, and carrying out the online adjustment of the thickness of the sliding mode boundary layer through the fuzzy adjuster. A closed-loop system controlled through the method can enable the actual attitude to be stably adjusted to a target attitude, and achieves the good robustness and control precision for a rotational inertia time varying effect and external disturbance. The method provides an effective means for the engineering implementation of the on-orbit refueling spacecraft attitude control.

Description

technical field [0001] The invention relates to the technical field of automatic control, in particular to an attitude control method of an on-orbit refueling spacecraft. Background technique [0002] On-orbit refueling of spacecraft refers to the rendezvous and docking with the spacecraft that needs to be replenished with propellant through a spacecraft carrying propellant, and then the propellant is transferred from the propellant to the propellant through the connected pipeline. The process of tank transfer to the target spacecraft's propellant tanks. On-orbit refueling technology has many advantages: through on-orbit refueling of application satellites, it can save the launch cost caused by carrying a large amount of propellant for the initial launch, prolong the service life of satellites, and avoid the huge cost of repeated launches of replacement satellites The cost has a high economic value; through the on-orbit refueling of the space mobile spacecraft, the large-sc...

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 廖瑛杨雅君文援兰郑宇昕薛高雄
Owner NAT UNIV OF DEFENSE TECH
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