An integrated control method for attitude and angular momentum of a tethered satellite

A technology for tethering satellites and a control method, which is applied in the directions of motor vehicles, space navigation equipment, space navigation equipment, etc., to achieve the effect of saving research and development costs, meeting market demands, and saving actuators

Active Publication Date: 2022-07-29
BEIJING INST OF CONTROL ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Tethered satellites pose great challenges to the attitude control of each single satellite due to the existence of tethers

Method used

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  • An integrated control method for attitude and angular momentum of a tethered satellite
  • An integrated control method for attitude and angular momentum of a tethered satellite
  • An integrated control method for attitude and angular momentum of a tethered satellite

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Experimental program
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Effect test

Embodiment

[0057] Suppose the tether connection point of the tethered satellite is on the satellite-Z plane, the tether tension is 0.14N, and there is a deviation of {374.922E-3,374.922E-3}m between the tension direction and the satellite mass center in the X and Y directions, Theoretical calculation shows that the tethering moment caused by this deviation will change the attitude of the satellite attitude with a roll angle of -27.92° and a pitch angle of 32°. The force analysis of the satellite is as follows: figure 2 shown. Using the control method of the present invention, the simulation effect is as follows image 3 and Figure 4 shown, where image 3 Indicates that the gravity gradient stabilization control is completed, Figure 4 Indicates that the unloading of the angular momentum of the system is completed. The simulation shows that the angular rate damping effect of the tether torque can stabilize the satellite attitude to the predetermined roll angle and pitch angle, and t...

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Abstract

An integrated control method for the attitude and angular momentum of a tethered satellite, comprising the following steps: realizing the stable control of the gravity gradient of the attitude of the tethered satellite based on the attitude angular rate damping of the tethered moment; There is a certain deviation in the tension direction, so as to form the unloading moment of the angular momentum of the momentum wheel, the angular momentum of the momentum wheel is quickly unloaded, and then the normal gravity gradient and stable attitude are restored after unloading, so as to complete the integrated control of the attitude and angular momentum of the tethered satellite. . The invention ensures the stable attitude of the tethered satellite and the unloading of the angular momentum of the actuator at the same time, and ensures that the tethered satellite always has the ability to adjust the attitude.

Description

technical field [0001] The invention relates to an integrated control method for the attitude and angular momentum of a tethered satellite, and belongs to the technical field of attitude control of a tethered satellite. Background technique [0002] Due to the existence of the tethered satellite, the attitude control of each single satellite has brought great challenges. The tension of the tether under different tension states is very different, and the direction of the tether tension changes with the relative attitude and relative position of the two satellites. Generally, it cannot pass the satellite's center of mass accurately. Therefore, the satellite attitude is always Affected by the disturbance of a tethered moment with great uncertainty, how to stabilize the satellite's attitude and ensure that the attitude actuator is always in an unsaturated state under the action of the tethered tension is the key problem that must be solved in the attitude control of the tethered...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/34
CPCB64G1/244B64G1/34B64G1/245
Inventor 陆栋宁谈树萍陈超雷拥军王淑一于强王绍凯李鹤徐子荔
Owner BEIJING INST OF CONTROL ENG
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