A low-power-consumption sun capture and directional attitude control method for magnetically controlled small satellites

A technology of attitude control and low power consumption, which is applied in the directions of space navigation equipment, space navigation aircraft, space navigation aircraft guidance devices, etc. problems such as small level, to achieve the effect of ensuring high-efficiency charging

Active Publication Date: 2022-02-01
JILIN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention solves the problem that the existing magnetic control satellite technology is limited by the magnitude of the magnetic control torque, and the direction of the magnetic control torque is limited by the earth's magnetic field at the position of the satellite, so that the magnetic control torque can only be positive in the direction of the earth's magnetic field. Problems such as generation in the intersecting plane, providing a low-power-consumption sun capture and directional attitude control method for magnetron satellites

Method used

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  • A low-power-consumption sun capture and directional attitude control method for magnetically controlled small satellites
  • A low-power-consumption sun capture and directional attitude control method for magnetically controlled small satellites
  • A low-power-consumption sun capture and directional attitude control method for magnetically controlled small satellites

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specific Embodiment approach 1

[0027] Specific implementation mode 1. Combination Figure 1 to Figure 5 To illustrate this embodiment, for a small satellite with a hexahedral configuration, it is equipped with a 0-1 solar sensor on each surface, and six 0-1 solar sensors cover the entire sky; a digital solar sensor is configured and installed On the largest sun-facing surface of the satellite; configure a magnetometer; configure a set of MEMS gyroscopes for measuring the satellite's three-axis attitude angular velocity information; configure a set of magnetic coils that can control the satellite's three axes.

[0028] A low-power-consumption sun capture and directional attitude control method for a magnetron satellite, the method is realized by the following steps:

[0029] Step 1: Obtain the magnetic field strength vector and attitude angular velocity vector under the star system according to the measurement information of the magnetometer and MEMS gyroscope;

[0030] Step 2: According to whether the sun ...

specific Embodiment approach 2

[0038] Specific embodiment two, combine Figure 1 to Figure 5 This embodiment is described. This embodiment is an embodiment of the method for capturing the sun with low power consumption and directional attitude control of a magnetron satellite described in Embodiment 1. The specific process is as follows:

[0039] Step 1: According to the measurement information of the magnetometer at the current moment, through the transformation of the magnetometer installation matrix, the magnetic field intensity vector at the current moment under the star system is obtained According to the measurement information of the MEMS gyroscope at the current moment, through the transformation of the MEMS gyroscope installation matrix, the attitude angular velocity vector of the star system relative to the inertial system at the current moment is obtained

[0040] Step 2: According to the current moment sun direction information obtained by the 0-1 sun sensor measurement, according to the pres...

specific Embodiment approach 3

[0056] Specific implementation mode three, this implementation mode is the embodiment of specific implementation mode two:

[0057] In this implementation, a certain type of magnetically controlled small satellite is taken as an example, and its moment of inertia matrix is ​​as follows:

[0058]

[0059] Set the maximum magnetic moment of the magnetic coil to 7Am 2 , and the attitude angular velocity at the initial moment of the simulation is [0,0,0]° / s. At the initial moment of the simulation, the sun is visible on the -Z and -Y planes of the satellite. During the sun-seeking and sun-aligning process of the satellite’s largest sail surface, the attitude angular velocity, magnetic control torque and output angle change curve of the digital sun sensor in the inertial system are as follows: image 3 , Figure 4 with Figure 5 shown. In the simulation time of about 207.5s, the satellite can rotate around the +Y axis and the -Z axis according to the set attitude angular ve...

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Abstract

A low-power-consumption sun capture and directional attitude control method for magnetically controlled small satellites, which relates to the field of satellite attitude control technology, and solves the problem that the existing magnetically controlled satellite technology is limited by the magnitude of the magnetically controlled torque and the direction of the magnetically controlled torque Restricted by the earth's magnetic field at the position of the satellite, etc., the magnetron torque can only be generated in a plane perpendicular to the direction of the earth's magnetic field. Sun sensor, and six 0‑1 sun sensors cover the whole sky; configure one digital sun sensor and install it on the largest sun-facing surface of the satellite; configure a magnetometer; configure for measuring the three-axis attitude of the satellite A set of MEMS gyroscopes for angular velocity information; a set of magnetic coils that can control the satellite's three axes. The invention designs a sun-seeking control logic, and proposes a closed-loop control method based on the angular velocity control of the small satellite to ensure that the small satellite can capture the sun with the largest sail surface under any initial attitude in the sunny area.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a method of using a space magnetic field and a satellite-borne magnetic coil to realize the capture and orientation control of a small satellite sailboard to the sun and ensure the energy supply of the satellite. Application of a low energy consumption satellite attitude control technology. Background technique [0002] In recent years, due to the development of high-tech aerospace technology such as microsystem technology, micromachines and micromachining technology, the development of small satellites has the technical characteristics of "faster, better and more economical". Its general functions can be used in multi-satellite networks, and it has broad application prospects in many fields such as modern communications, aerospace, and the environment. [0003] The small satellite attitude control subsystem is one of the important guarantee subsystems for the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/36B64G1/44
CPCB64G1/244B64G1/363B64G1/366B64G1/443B64G1/245
Inventor 范国伟张刘章家保王文华朱杨张帆宋莹赵寰宇
Owner JILIN UNIV
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