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Low-power-consumption sun-facing capture and orientation attitude control method for magnetic control small satellite

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. internal problems, to achieve the effect of ensuring energy supply

Active Publication Date: 2020-11-03
JILIN UNIV
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  • Summary
  • 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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  • Low-power-consumption sun-facing capture and orientation attitude control method for magnetic control small satellite
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  • Low-power-consumption sun-facing capture and orientation attitude control method for magnetic control small satellite

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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 and 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 vel...

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Abstract

The invention discloses a low-power-consumption sun-facing capture and orientation attitude control method of a magnetic control small satellite, relates to the technical field of satellite attitude control, and solves the problems that the existing magnetic control satellite technology is limited by a small magnetic control moment magnitude, the direction of the magnetic control moment is limitedby an earth magnetic field and the like at the position of the satellite, and therefore, the magnetic control moment can only be generated in a plane orthogonal to the direction of the earth magneticfield. Aiming at a hexahedral small satellite, the method comprises the steps: enabling each surface of the hexahedral small satellite to be provided with a 01-type sun sensor, wherein six 01-type sun sensors cover the whole celestial sphere; configuring one digital sun sensor and installing the digital sun sensor on the maximum sun-facing surface of the satellite; configuring a magnetometer; configuring a set of MEMS gyroscopes for measuring three-axis attitude angular velocity information of the satellite; and configuring a set of magnetic coils capable of controlling three axes of the satellite. The invention designs a sun-finding control logic, provides a control method based on a minisatellite angular velocity control closed loop, and ensures that the minisatellite can realize sun-facing capture of a maximum sailboard surface under any initial attitude of a sunshine 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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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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