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A Reliable Solar Panel Autonomous Tracking Sun Control Method

A control method and autonomous tracking technology, applied in non-electric variable control, position/direction control, control/regulation system, etc., can solve problems such as influence of motor life, complex software interface, lead or lag, etc., to improve reliability and security, simplifying hardware configuration, and facilitating engineering implementation

Active Publication Date: 2018-07-24
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Sailboard control first needs to obtain the relationship between the sun position and the sailboard position, which can be directly measured by installing a simulated solar sensor on the sailboard on the satellite, or can be obtained by measuring the sun vector and the current position of the sailboard by installing a sensor on the satellite body, but The former of these two methods brings complex satellite hardware design, while the latter brings complex software interface, that is, it needs to rely on sensor measurement information. Therefore, in order to simplify satellite design and software interface, a design is designed that does not require sensor measurement information and only requires satellite orbits. Method for controlling the rotation angle of the sailboard based on the current position of the sailboard
[0003] According to the working orbit of the satellite, the working modes of sailboard drive control include cruise mode, hold mode, incremental mode and automatic zero mode. There is a deviation from the theoretical orbit, and the orbit is affected by perturbation. When the sailboard rotates at a fixed angular velocity, it will lead or lag behind the target angle after a period of time, resulting in poor alignment accuracy and unable to meet energy needs. Therefore, the sailboard drive mechanism needs to be switched to Incremental mode, rotate at a fast angular speed or switch to hold mode. The control strategy design ensures that the sailboard meets the accuracy of the sun and at the same time ensures that the sailboard does not stop frequently. Frequent stalls not only disturb the attitude, but also affect the life of the motor. Therefore, it is necessary to design a control strategy to ensure that the sailboard does not switch modes frequently during the tracking process

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  • A Reliable Solar Panel Autonomous Tracking Sun Control Method
  • A Reliable Solar Panel Autonomous Tracking Sun Control Method
  • A Reliable Solar Panel Autonomous Tracking Sun Control Method

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Embodiment Construction

[0044] The following is a typical example of a certain high-orbit satellite, in conjunction with the accompanying drawings to describe the preferred embodiment of the present invention, the satellite is an inclined geosynchronous orbit satellite, orbital height 35786km, orbital inclination 55 degrees, eccentricity ≤ 0.005, solar panel installation satellite On the ±Y side, the control mode switching diagram of sailboard control is as follows figure 1 shown.

[0045] According to the control strategy in the manual, the sailboard is automatically tracked and controlled. The on-orbit data shows that the control accuracy of the sailboard to the sun is within 3 degrees. Through this strategy, the number of mode switching is significantly reduced. The results of the sailboard’s on-orbit control are as follows: Figure 5 shown.

[0046] The description and application of the invention herein is illustrative and is not intended to limit the scope of the invention to the above-descri...

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Abstract

The invention discloses a reliable method for controlling a panel to autonomously track the sun. To meet the energy requirement of a satellite, the solar panel having a one-dimension rotation function is installed on the satellite, and the normal of the panel is made to point to the sun through controlling the rotation of the panel and the attitude of the satellite. According to the invention, no sun sensor is required to be installed on the panel, the information of the solar vector and the current attitude of the satellite are neither needed to be detected by an on-satellite sensor, the rotation target angle of the panel is calculated only according to a sun model and the satellite orbit, then different control areas are set through designing reasonable angle thresholds, the panel is controlled to work at different modes according to the division of the control areas, the switching frequency of the panel among different modes can be lowered through choosing reasonable thresholds, and thus the situation that the panel frequently stops and rotates to disturb the satellite attitude and influence the working life of a motor is avoided. The method for controlling the solar panel to autonomously track the sun is simple and effective, low in implementation cost, and convenient for engineering implementation.

Description

technical field [0001] The invention belongs to the technical field of spacecraft control, and relates to a simple and reliable solar panel self-tracking sun control method. Background technique [0002] In order to meet the energy requirements of the satellite, a one-dimensional rotating solar panel is installed on the satellite. The satellite controls the rotation of the star and the rotation of the sail to make the normal of the sail point to the sun. Sailboard control first needs to obtain the relationship between the sun position and the sailboard position, which can be directly measured by installing a simulated solar sensor on the sailboard on the satellite, or can be obtained by measuring the sun vector and the current position of the sailboard by installing a sensor on the satellite body, but The former of these two methods brings complex satellite hardware design, while the latter brings complex software interface, that is, it needs to rely on sensor measurement in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/44G05D3/10
CPCB64G1/44G05D3/105
Inventor 武国强张锐林宝军熊淑杰白涛王昊光秦贵军
Owner SHANGHAI ENG CENT FOR MICROSATELLITES