Stable control system and method for satellite spinning around sun

A spin stabilization and control system technology, applied in the field of satellite control, can solve the problems of low-cost and convenient satellite-to-day spin stabilization control, and achieve energy acquisition, passive stability, reliability and safety. Guaranteed effect

Active Publication Date: 2016-09-28
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Claims
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Problems solved by technology

[0003] In view of the above-mentioned shortcomings of the prior art, the purpose of the present invention is to provide a satellite-to-sun spin stabilization control system and method, which is used to solve the problem of low-cost and convenient satellite-to-sun spin stabilization control in the prior art. The problem

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  • Stable control system and method for satellite spinning around sun
  • Stable control system and method for satellite spinning around sun
  • Stable control system and method for satellite spinning around sun

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Embodiment Construction

[0021] Embodiments of the present invention are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other.

[0022] It should be noted that the diagrams provided in the following embodiments are only schematically illustrating the basic ideas of the present invention, and only the components related to the present invention are shown in the diagrams rather than the number, shape and number of componen...

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Abstract

The invention provides a stable control system and method for a satellite spinning around the sun. A simulation sun sensor is used for measuring a sun vector under a satellite body system; a triaxial magnetometer is used for measuring a terrestrial magnetism vector under a satellite body; a controller is electrically connected with the simulation sun sensor and the triaxial magnetometer and used for obtaining the sun vector and the terrestrial magnetism vector, judging the current mode of the satellite and generating and sending a control command according to the current mode; and the magnetic torquer is used for outputting the corresponding magnetic torque according to the control command sent by the controller. By the adoption of the system and method, the satellite can stably spin around the sun through the high-reliability and low-power-consumption execution component magnetic torquer, and the satellite is passively stabilized and obtains energy. A guarantee is provided for the reliability and the safety of the satellite, and the defect that large-power-consumption and consumptive components such as a propeller and a flywheel are adopted in a satellite in the prior art is overcome.

Description

technical field [0001] The invention relates to the field of satellite control, in particular to a satellite-to-sun spin stabilization control system and method. Background technique [0002] To realize satellite spin orientation in the prior art, the nutation angle and precession angle of the satellite are measured by the nutation sensor, and the chapter precession is controlled by some kind of damper, and the angular velocity sensor is required to measure the satellite The angular velocity of the spin axis to maintain a stable spin of the satellite's spin axis. At present, the precession control of spin satellites usually adopts jet and other actuators, which consume fuel, resulting in limited life and high cost. Contents of the invention [0003] In view of the above-mentioned shortcomings of the prior art, the purpose of the present invention is to provide a satellite-to-sun spin stabilization control system and method, which is used to solve the problem of low-cost a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/36
CPCB64G1/10B64G1/363B64G1/366
Inventor 刘善伍容建刚况思然高海云张学钢
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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