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Area coverage control method for offset momentum satellite

A bias momentum and area coverage technology, applied in the field of satellite control, can solve the problems of increasing satellite cost and increasing satellite weight

Pending Publication Date: 2021-05-07
BEIJING GUODIAN GAOKE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the average current generated by the above-mentioned solar cell array drops to 63.69%, the number of solar cells that needs to be increased is 50% of the original number, which increases the weight of the satellite and also increases the cost of the satellite

Method used

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  • Area coverage control method for offset momentum satellite
  • Area coverage control method for offset momentum satellite
  • Area coverage control method for offset momentum satellite

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Embodiment Construction

[0017] In order to make the content of the present invention clearer and easier to understand, the content of the present invention will be described in detail below in conjunction with specific embodiments and accompanying drawings.

[0018]

[0019] For a satellite operating in a sun-synchronous orbit, no matter when its descending node is, its important feature is the component S of the sun vector S on the Y axis of the satellite body coordinate system (indicated by the XYZ coordinate system) y Unchanged: S y =S×cosθ, that is to say, the angle θ between the sun vector and the Y axis of the satellite body coordinate system remains unchanged.

[0020] In the inertial coordinate system, the sun vector is fixed, while the orbital coordinate system takes the Y axis as the center and the orbital angular velocity ω 0 rotate. The satellite body coordinate system completely coincides with the orbit coordinate system without attitude error, then in the satellite body coordinate s...

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Abstract

The invention provides an area coverage control method for an offset momentum satellite, which comprises the following steps that a first momentum wheel, a second momentum wheel and a third momentum wheel are adopted to execute attitude control in an offset momentum control mode, the nominal angular momentum directions of the first momentum wheel and the second momentum wheel are in a YOZ plane of a satellite body system and are distributed on two sides of a Y axis, the included angle with the Y axis is 45 degrees; the nominal angular momentum direction of the third momentum wheel is in the Z axis and is a backup of the two V-shaped momentum wheels; and the three-axis axial magnetic torquer is used for unloading the momentum wheel.

Description

technical field [0001] The invention relates to the field of satellite control, in particular to an area coverage control method of a bias momentum satellite. Background technique [0002] Communication satellites generally provide all-weather services around the world. Due to the relatively large load power, the batteries and solar wings carried by the satellites are also relatively large. In order to meet the needs of global all-weather service, the load is turned on 24 hours a day, and its antenna pointing center has been pointing to the center of the earth, the solar wing is fixed on the ±Y plane of the satellite, and equipped with a solar panel drive mechanism (SADA), Drive the solar wings so that the solar cell array is always pointing to the sun, so that the maximum light energy can be converted into electrical energy to charge the battery. [0003] However, since SADA is very expensive, and once used, it will become a single point of failure source in satellite reli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/244
Inventor 吕强
Owner BEIJING GUODIAN GAOKE TECH CO LTD
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