Solar sailboard variable-speed driving method under yaw guidance of inclined orbit satellite

A solar panel and variable speed drive technology, applied in the direction of non-electric variable control, instrument, control/adjustment system, etc., can solve the problem of high cost of two-dimensional drive mechanism, and achieve the effect of cost saving and satellite energy protection

Active Publication Date: 2021-04-13
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

However, the cost of the two-dimensional drive mechanism is relative...

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  • Solar sailboard variable-speed driving method under yaw guidance of inclined orbit satellite
  • Solar sailboard variable-speed driving method under yaw guidance of inclined orbit satellite
  • Solar sailboard variable-speed driving method under yaw guidance of inclined orbit satellite

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Embodiment Construction

[0031] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments. Advantages and features of the present invention will be apparent from the following description and claims. It should be noted that the drawings are all in a very simplified form and use imprecise ratios, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention.

[0032] Orbits with little change in the angle between the sun and the orbital plane include sun-synchronous orbits, geostationary orbits, etc. For satellites operating in this type of orbit, the solar panels are driven in the opposite direction of the orbital angular velocity to ensure the position of the panels and the sun relatively fixed. For a satellite operating on an inclined orbit, the angle range between the sun and the satellite’s orbital plane is very large. If the satellite’s yaw direction attitude d...

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Abstract

The invention discloses a solar sailboard variable-speed driving method under yaw guidance of an inclined orbit satellite. The solar sailboard variable-speed driving method comprises the following steps: calculating a solar altitude angle and a satellite orbit angle in real time; calculating a theoretical rotating angle and a theoretical driving angular speed of the solar sailboard at the current moment in real time according to the solar altitude angle and the satellite orbit angle; calculating an angle needing to be driven by the solar sailboard at the current moment according to the theoretical rotating angle of the solar sailboard at the current moment; and selecting the gear closest to the theoretical driving angular speed of the solar sailboard at the current moment in the gears of the solar sailboard driving mechanism as a center value, and determining the micro-amplitude adjustment amount according to the angle needing to be driven by the solar sailboard at the current moment, so that the driving angular speed of the solar sailboard at the current moment is obtained. The solar sailboard adopts a variable angular velocity driving method, so that the solar sailboard is always perpendicular to the sun, and satellite energy is guaranteed.

Description

technical field [0001] The invention relates to an attitude control technology of an inclined-orbit satellite, in particular to a variable-speed driving method for a solar panel under the yaw guidance of an inclined-orbit satellite. Background technique [0002] With the rapid development of the aerospace industry, the functions of satellites are becoming more and more abundant, and the payload power carried is also increasing. There is also a precise range for the accuracy of solar panels to align with the sun. If a satellite in an inclined orbit only drives the solar panels in the opposite direction of the orbital angular velocity, as the altitude angle of the sun changes, the angle between the solar panels and the sun will become larger and larger, which cannot meet the requirements of the on-board load, so the yaw The direction must be guided by periodic or real-time steering maneuvers as the sun's altitude changes. Otherwise, the solar panels need to be driven two-dime...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0833Y02E10/50
Inventor 王蕊王静吉张小伟修艳红周静静陈银河李正军
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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