Magnetic control sun capturing method in consideration of solar angle change rate and variable control factor weight

A technology of sun angle and rate of change, applied in feedback control, transportation and packaging, space navigation equipment, etc., can solve problems such as the influence of satellite solar power supply, long-term control convergence instability, and unsatisfactory control of sun angle accuracy

Active Publication Date: 2018-09-18
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology

[0006] Aiming at the problems in the prior art that the sun-oriented magnetron control algorithm based on satellite reaction wheel spin bias plus magnetron control has long-term control convergence instability, and the unsatisfactory control of the sun angle accuracy causes the satellite solar power supply to be affected, according to the present invention An embodiment of the present invention provides a magnetron sun capture method considering the sun angle rate of change and control factor weight variable, including: carrying out the calculation of the modulus of the sun angle, the sun angular velocity and the magnetic vector rate of change; performing the sun vector calculation validity Judgment; wh

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  • Magnetic control sun capturing method in consideration of solar angle change rate and variable control factor weight
  • Magnetic control sun capturing method in consideration of solar angle change rate and variable control factor weight

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Embodiment Construction

[0037] In the following description, the present invention is described with reference to various examples. Those skilled in the art will recognize, however, that the various embodiments may be practiced without one or more of the specific details, or with other alternative and / or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure aspects of the various embodiments of the invention. Similarly, for purposes of explanation, specific quantities, materials and configurations are set forth in order to provide a thorough understanding of embodiments of the invention. However, the invention may be practiced without these specific details. Furthermore, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.

[0038] In this specification, reference to "one embodiment" or "the embodi...

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Abstract

The invention discloses a magnetic control sun capturing method in consideration of a solar angle change rate and a variable control factor weight. The method comprises the steps of calculating a solar angle, a solar angular velocity and modulus of a magnetic vector change rate; performing sun vector calculation validity determining; when sun vector calculation is effective, performing moment application direction calculation based on a flywheel rotation starting offset finishing condition; performing magnetic moment application direction calculation, and calculating an included angle betweenthe magnetic moment and the moment direction; determining whether the included angle between the magnetic moment and the moment direction is in a range between an upper limit and a lower limit; when the included angle between the magnetic moment and the moment direction is in the range between the upper limit and the lower limit, calculating a magnetic control output according to a rate and solarangle control and solar angle speed compensation algorithm; and performing amplitude limitation on a magnetic control output magnetic moment.

Description

technical field [0001] The invention relates to the field of satellite attitude control, in particular to a magneto-controlled sun capture method that considers the rate of change of the sun angle and the variable weight of the control factor. Background technique [0002] The satellite needs to keep the sail panels oriented to the sun under the constraints of certain working conditions. For example, when the satellite’s single machine fails and other attitude control abnormalities enter the safe mode, it is necessary to keep the sail panels oriented to the sun to ensure the energy security of the satellite. [0003] Usually, when the satellite enters the safe mode, it generally adopts the propulsion control or the method based on the magnetic control control to maintain the orientation to the sun. The satellites controlled by propulsion control are limited by propulsion reliability, fuel and other limitations, so it is not suitable for long-term sun-oriented control, and so...

Claims

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Application Information

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IPC IPC(8): G05D3/12
CPCB64G1/283B64G1/44
Inventor 阳应权陆姗姗万松吴子轶李晓红李东刘爽齐凯华张静
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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