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Control method for orbit and attitude of satellite

An attitude control and orbit control technology, applied in the field of satellite orbit and attitude control, can solve the problems of multi-attitude control fuel, affecting orbit control accuracy, and under-actuated control of satellite jet control, etc. Effect

Active Publication Date: 2013-11-20
BEIJING INST OF CONTROL ENG
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Problems solved by technology

During the orbiting process of the spacecraft, once the jet engine of a star axis fails to work due to some fault, the satellite jet control becomes an underactuated control problem, and the previous jet control method is no longer applicable
In any case, once there is a large disturbance moment in the orbit control process, it will consume more fuel for attitude control and even affect the accuracy of orbit control
[0003] At home and abroad, a lot of research has been carried out mainly on the orbit change strategy of orbit control. The attitude control strategy is only based on the control stability and attitude control accuracy research under full drive control, and the research on the large disturbance torque of the orbit control jet process. little

Method used

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  • Control method for orbit and attitude of satellite

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Embodiment Construction

[0025] The present invention will be further introduced below in conjunction with the accompanying drawings.

[0026] figure 1 Shown is the orbit and attitude control method of the present invention, and the method of the present invention will be further described below in conjunction with the embodiments of the present invention.

[0027] (1) Determine the track control disturbance torque

[0028] Due to the thrust deflection and lateral movement of the orbit control engine, installation error, and movement of the center of mass of the star, a large disturbance moment may be generated when the orbit control engine jets, causing the attitude of the star to change.

[0029] Embodiments of the present invention include at least the following two methods for determining the orbit control disturbance torque:

[0030] 1) Model-based analysis method: control the engine installation position according to the track Thrust magnitude and direction The position of the center of ma...

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Abstract

The invention discloses a control method for the orbit and the attitude of a satellite, which is characterized by comprising the following steps of: determining disturbance moment for the control of the orbit; determining a control strategy for the attitude according to the disturbance moment, wherein the control strategy for the attitude comprises a control mode of air jet or a control mode of angular momentum exchange; determining an air jet strategy for the control of the orbit according to the control strategy for the attitude; and carrying out the control of the orbit and the attitude according to the air jet strategy. The method can be suitable for a satellite with large disturbance moment in the orbit-controlled air jet process.

Description

technical field [0001] The invention belongs to the technical field of satellite attitude and orbit control, and relates to a satellite orbit and attitude control method. Background technique [0002] During the orbit control process of the spacecraft, the orbit-changing engine installed on the spacecraft ignites in a certain way to generate thrust. The orbit-changing accuracy depends on the performance of the engine, the control of the ignition time and the control of the direction of the thrust vector. The latter is mainly controlled by the spacecraft. Attitude control designers generally have strict restrictions on the engine installation position error, engine thrust eccentricity error, etc., and design a corresponding attitude control scheme. However, in the past, spacecraft generally used attitude control engines as orbits. The attitude control actuator of the control process. Jet attitude control has a large torque and no angular momentum constraints. Generally, the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/26
Inventor 王新民袁军张俊玲马世俊魏春岭赵性颂周剑敏孙水生刘捷王淑一刘其睿
Owner BEIJING INST OF CONTROL ENG
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