Attitude control method applied to centroid transverse moving spacecraft

A space vehicle and attitude control technology, which is applied in the field of space vehicle attitude control, can solve the problems of no description or report, no data collected, etc., and achieve the effect of good control, elimination of aircraft attitude interference, and accurate guidance

Active Publication Date: 2013-05-29
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] At present, there is no description or report of similar technology with the present invention, and similar materials at home and abroad have not been collected yet.

Method used

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  • Attitude control method applied to centroid transverse moving spacecraft
  • Attitude control method applied to centroid transverse moving spacecraft
  • Attitude control method applied to centroid transverse moving spacecraft

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Embodiment Construction

[0016] The present invention will be described in further detail below in conjunction with accompanying drawings and examples.

[0017] like figure 1 Shown is a schematic diagram of the lateral movement of the spacecraft's center of mass. Limited by the structural layout and manufacturing process of the spacecraft, the spacecraft usually has a certain degree of center-of-mass shift, and the phenomenon of center-of-mass shift will be intensified with the consumption of fuel and the separation of loads.

[0018] like figure 2 Shown is the description of the thrust vector, the installation position of the attitude control engine, the position of the center of mass of the spacecraft, etc. in the center of mass translation coordinate system SXYZ. The spacecraft relies on the thrust vector provided by the swing engine to realize the orbit control and the attitude control of the yaw and pitch channels. The attitude control of the roll control channel is installed along the circumf...

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Abstract

The invention provides an attitude control method applied to a centroid transverse moving spacecraft. According to the method, quaternions are adopted to describe rotation of an engine spray pipe relative to a spacecraft body, and an expectation attitude of the spacecraft, meeting guidance requirements, is determined based on the guidance direction and the rotating quaternions; simulation eulerian angles describing attitude deviation of the spacecraft are brought in, and a variable structure attitude control law is built based on an attitude motion model of the simulation eulerian angles; and the spacecraft attitude is controlled to be in the expectation attitude, so orbital transfer thrust direction guidance can be guaranteed. The attitude control method solves the control law design problem that attitude control is carried out for the spacecraft with a centroid moving transversely through adoption of thrust vectors and an attitude control engine, the adopted attitude description avoids singularity owned by eulerian angle attitude description inherently, and three components of the attitude description have obvious physical significance; and the attitude control law based on the attitude description is simple in form and good in control effect.

Description

technical field [0001] The invention relates to the technical field of attitude control of spacecraft, and is especially suitable for the attitude control of spacecraft with obvious barycenter lateral movement during orbital operation. Background technique [0002] The arc section that the launch vehicle flies through during the process of delivering the load into orbit is relatively short, and there is no real large-angle attitude change. Therefore, the attitude feedback control law based on Euler angles can meet its attitude control requirements. However, the range of attitude changes of the spacecraft during its orbital operation is large, and the attitude dynamic equation described by Euler angles cannot avoid the singularity problem; although the attitude quaternion avoids the singularity phenomenon, it cannot directly reflect the attitude change. [0003] If the multiple payloads carried by the spacecraft are arranged in parallel and need to be released one by one, the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/42
Inventor 夏喜旺刘汉兵杜涵
Owner SHANGHAI AEROSPACE SYST ENG INST
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