A satellite spin stabilization control system and method for 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 spin stabilization control to achieve the effect of energy acquisition, passive stability and low power consumption

Active Publication Date: 2018-10-16
SHANGHAI ENG CENT FOR MICROSATELLITES
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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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  • A satellite spin stabilization control system and method for sun
  • A satellite spin stabilization control system and method for sun
  • A satellite spin stabilization control system and method for sun

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Embodiment Construction

[0021] The following describes the implementation of the present invention through specific specific examples. 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 embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and the features in the embodiments can be combined with each other if there is no conflict.

[0022] It should be noted that the illustrations provided in the following embodiments only illustrate the basic idea of ​​the present invention in a schematic way, so the figures only show the components related to the present invention instead of the actual implementation of the number, shape and For...

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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 present invention relates to the field of satellite control, in particular to a system and method for controlling satellite spin stability to the sun. Background technique [0002] In the prior art to realize the satellite spin orientation, a nutation sensor is required to measure the nutation angle and precession angle of the satellite, and a damper is used to control the nutation precession, and an angular velocity sensor is required to measure the satellite The angular velocity of the spin axis is used to maintain the stable spin of the satellite's spin axis. At present, the precession control of spin satellites usually uses actuators such as jets, which consume fuel, which results in limited life and high cost. Summary 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-solar spin stabilization control system and method, which is used to solve the i...

Claims

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Application Information

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Patent Type & Authority Patents(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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