Long-term Sun Tracking Control Method for Satellites

A tracking control and satellite technology, which is applied in the field of long-term sun tracking control of satellites, can solve the problem of attitude capture actuator saturation, etc., and achieve the effect of reducing accumulation and maintaining long-term sun tracking

Active Publication Date: 2022-01-28
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to provide a long-term satellite tracking control method to solve the problem that the attitude capture of the satellite safety mode with large-scale deployment components such as large-scale antennas and solar arrays is easy to cause saturation of the actuator

Method used

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  • Long-term Sun Tracking Control Method for Satellites
  • Long-term Sun Tracking Control Method for Satellites
  • Long-term Sun Tracking Control Method for Satellites

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Embodiment Construction

[0038] The following is attached figure 1 and specific embodiments A method for long-term daily tracking control of a satellite according to the present invention will be further described in detail. The advantages and features of the present invention will become clearer from the following description. It should be noted that the drawings are in a very simplified form and all use imprecise scales, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention. In order to make the objects, features and advantages of the present invention more comprehensible, please refer to the accompanying drawings. It should be noted that the structures, proportions, sizes, etc. shown in the drawings attached to this specification are only used to match the content disclosed in the specification, for those who are familiar with this technology to understand and read, and are not used to limit the implementation of the present inven...

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Abstract

The invention discloses a long-term sun-tracking control method for a satellite, the method comprising: controlling the X and Y axes of the satellite to realize the -Z-axis tracking of the satellite; the Z-axis maneuvering of the satellite keeps the X-axis of the satellite at within the orbital plane. The invention establishes a stable region of the satellite by controlling the X axis of the satellite to the orbital plane, reduces the accumulation of the angular momentum of the star, and solves the problem that the gravity gradient moment of the satellite equipped with large-scale antennas, solar arrays and other large-scale expansion components is large. The problem of not being able to keep track of the day for a long time.

Description

technical field [0001] The invention relates to the field of satellite attitude control, in particular to a long-term sun tracking control method for satellites. Background technique [0002] Satellites are generally designed with a safety mode to ensure the safety of the satellite in the event of a serious failure in orbital operation. One of the safety modes is to control the satellite’s solar array against the sun through attitude control to ensure the energy of the satellite, and wait for the fault to be cleared on the ground before returning to the normal working mode. [0003] For satellites equipped with large-scale deployed components such as large-scale antennas and solar arrays, the product of inertia is relatively large, resulting in a large gravity gradient moment on the satellite. When the satellite enters the safe mode and turns to sun orientation and tracking, due to the effect of the gravity gradient moment, the momentum actuator of the satellite is saturate...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/244
Inventor 张涛郭思岩高四宏林新迪
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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