Satellite attitude stability control method and device

A stability control method and a technology of a stability control device, which are applied in the direction of aerospace vehicle guidance devices, etc., can solve the problems of not switching between different stabilization modes, easy to lose attitude reference, and single stabilization mode, so as to achieve good engineering application prospects and promotion value, save the entire star resource, and improve the effect of flexibility

Active Publication Date: 2014-10-01
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology

[0003] The attitude stabilization methods of existing in-orbit satellites are all single stabilization methods, or bias momentum stabilization mode, or zero momentum stabilization mode, and do not have the function of switching between different stabilization modes
If only the bias momentum stabilization mode is used, the large-angle maneuvering and high-precision control requirements durin

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  • Satellite attitude stability control method and device
  • Satellite attitude stability control method and device

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Embodiment Construction

[0016] The specific implementation of a satellite attitude stabilization control method and device provided by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0017] see figure 1 As shown, a satellite attitude stabilization control method includes the following steps: S10: Obtain the current stabilization mode of the satellite attitude; S12: Receive a switching instruction sent by the ground according to the task requirements, and the switching instruction includes switching information of the stabilization mode to be executed; S14: Determine whether the stabilization mode to be executed is the same as the current stabilization mode, and if not, execute step S16; S16: Switch the current stabilization mode to the stabilization mode to be executed, and perform satellite attitude stabilization control.

[0018] Step S10: Obtain the current stabilization mode of the satellite attitude.

[0019] The current stable mode is on...

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Abstract

The invention discloses a satellite attitude stability control method and device. The method comprises the steps of: (1) obtaining a present satellite attitude stability mode, wherein the present stability mode is one of a zero-momentum stability mode or a bias-momentum stability mode; (2) receiving a switching instruction sent from the ground according to the task requirement, wherein the switching instruction includes switching information of a stability mode required to be executed, and the stability mode required to be executed is one of the zero-momentum stability mode or the bias-momentum stability mode; (3) judging if the stability mode required to be executed is the same with the present stability mode, if not, performing the step (4); and (4) switching the present stability mode to the stability mode required to be executed, and performing the satellite attitude stability control. The method realizes the free switching between the bias-momentum stability and the zero-momentum stability through introducing the ground intervention according to the instruction sent from the ground, so that the control system flexibility is improved.

Description

technical field [0001] The invention relates to the technical field of aerospace measurement and control, in particular to a satellite attitude stabilization control method and device suitable for micro-satellites with both bias momentum and zero-momentum stabilization modes. Background technique [0002] At present, there are two mature methods of satellite attitude stabilization, bias momentum stabilization and zero momentum stabilization. The bias momentum stabilization mode has the fixed axis in one direction, so it has a strong interference suppression ability. At the same time, the bias momentum stabilization mode has the characteristics of simple configuration and high reliability; the zero momentum stabilization mode does not have the gyro axis fixation , usually used in the three-axis stability control stage, has the characteristics of high control precision. [0003] The attitude stabilization methods of existing in-orbit satellites are all single stabilization me...

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Application Information

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IPC IPC(8): B64G1/28B64G1/36B64G1/24
Inventor 李晓红刘爽万松阳应权李东吴子轶
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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