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Magnetron Non-Spin Sun Orientation Method

A non-spin and magnetron technology, applied in the power supply system of space navigation vehicle and other directions, can solve the problem of too large angle error with respect to the sun, and achieve the effect of small amount of calculation, elimination of adverse effects, and easy engineering.

Active Publication Date: 2022-06-07
SHANDONG INST OF AEROSPACE ELECTRONICS TECH
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The magnetron non-spin alignment method of the present invention is to solve the problems existing in the above-mentioned prior art and provide a method for implementing the magnetron non-spin alignment alignment in the whole course of the orbit. Compared with the existing magnetron alignment Due to the shortcomings of the sun method, it can effectively solve the problem of excessive angle error caused by the gyro torque brought by the rotational angular velocity of the star and the change of the magnetic field on the orbital plane, so as to realize the illumination area under the non-spin magnetron Fast and accurate adjustment to the sun

Method used

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  • Magnetron Non-Spin Sun Orientation Method

Examples

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Embodiment 1

[0052] Example 1, as figure 1 As shown, the magnetron non-spin sun orientation method is to realize the uniaxial sun orientation adjustment by controlling the magnetic moment of the magnetic torque device in the plane torque of the magnetic field strength as the normal vector, and the desired control torque T dir The calculation formula is as follows:

[0053]

[0054] where , represents the dot product of the vector,

[0055] × means cross product,

[0056] |·| represents the norm of the vector,

[0057] sgn( ) is a symbolic function,

[0058] J 0 ∈R 3×3 is the moment of inertia of the satellite ground calibration,

[0059] k 1 ,k 2 ,k 3 ∈R 1 is the control coefficient of the magnetron-to-day algorithm,

[0060] θ∈R 1 is the solar vector S of the satellite system obtained by measurement or calculation m ∈R 3×1 and the expected solar vector S of this system d ∈R 3×1 the angle between

[0061] ω mag ∈R 3×1 represents the angular velocity component of the a...

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Abstract

The magnetron non-spin alignment method of the present invention provides a method for implementing the magnetron non-spin alignment method on-orbit, which can effectively Solve the problem of too large angle error caused by the gyro torque brought by the rotational angular velocity of the star and the change of the magnetic field on the orbital surface, so as to realize the fast and accurate adjustment of the sun in the illumination area under non-spin magnetron. The magneto-controlled non-spin orientation to the sun method is to realize the single-axis orientation adjustment to the sun by controlling the magnetic moment of the magnetic torque device when the magnetic field strength is the normal vector plane torque.

Description

technical field [0001] The invention relates to a method for adjusting a windsurfing board of an in-orbit satellite to implement magnetron non-spinning sun orientation, belonging to the field of aerospace design. Background technique [0002] With the rapid development of domestic satellite attitude and on-orbit control technology, the energy security performance and platform survival time of on-orbit satellites have been continuously improved. For in-orbit micro-nano satellites, when there are some non-autonomous problems that can be solved, the platform usually transfers the satellite to a mode with minimal energy consumption to wait for the ground to process and ensure the safety of the satellite in orbit. For example, if the high-power loads and actuators on the satellite are turned off, the lowest energy consumption configuration is adopted and the magnetron sun-facing mode is adopted, so as to ensure that the sunlight enters the solar panel according to the set angle i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/44
CPCB64G1/44
Inventor 李明翔张众正王菲董兴涛张爽姜宇鹏
Owner SHANDONG INST OF AEROSPACE ELECTRONICS TECH