Integrated control method for attitude and angular momentum of 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, saving actuators, and meeting market demands

Active Publication Date: 2021-08-06
BEIJING INST OF CONTROL ENG
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  • Abstract
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  • Claims
  • Application Information

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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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  • Integrated control method for attitude and angular momentum of tethered satellite
  • Integrated control method for attitude and angular momentum of tethered satellite
  • Integrated control method for attitude and angular momentum of tethered satellite

Examples

Experimental program
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Effect test

Embodiment

[0057] Assuming that the tether connection point of the tethered satellite is on the satellite-Z plane, the tension of the tether is 0.14N, and there is a deviation of {374.922E-3,374.922E-3}m between the tension direction and the center of mass of the satellite in the X and Y directions. Theoretical calculations show that the tether moment caused by this deviation will cause the attitude of the satellite attitude to change 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 stability 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 in conjunction with the tether torque can stabilize the attitude of the satellite to th...

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Abstract

The invention discloses a tethered satellite attitude and angular momentum integrated control method. The method comprises the following steps that gravity gradient stable control of tethered satellite attitude is realized based on attitude angular rate damping of tether moment; the attitude control torque is utilized to make the center of mass of the whole satellite deviate from the tension direction of the tether, so the unloading torque of the angular momentum of the momentum wheel is formed, the angular momentum of the momentum wheel is rapidly unloaded, the attitude with the stable normal gravity gradient is recovered after unloading, and integrated control over the attitude and the angular momentum of the tether satellite is completed. The method ensures that the attitude of the tethered satellite is stable and the angular momentum of the execution mechanism is unloaded at the same time, and ensures that the tethered satellite always has the attitude adjustment capability.

Description

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

Claims

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Application Information

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Patent Type & Authority Applications(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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