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Space debris lateral angular velocity suppression and spin direction control method

A technology of lateral angular velocity and direction control, which is applied in transportation and packaging, aerospace vehicle guidance devices, aerospace equipment, etc., and can solve the problem of lack of satellites

Active Publication Date: 2019-02-12
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

[0004] The innovation point and difficulty of this technology is that the abandoned satellites captured by the rope net have no actuators that can output torque, and the attitude of the satellite can only be controlled by the tension of the tether.

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  • Space debris lateral angular velocity suppression and spin direction control method

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Embodiment Construction

[0096] Attached below figure 1 , 2 , 3, 4, 5, 6, 7 are further detailed as follows to the content of the invention:

[0097] Firstly, the necessary assumptions are made on the system, and the dynamic modeling of the system is carried out. Then the dynamic equation of the system shimmy and the attitude dynamic equation of the target star are deduced. Then design two constant tension switching controllers and PD controllers. Further analysis whether the switching control is sustainable and the stability of the system, and under what circumstances the lateral angular velocity of the target star will be suppressed. Finally, the designed model is combined with the controller, and the numerical simulation is carried out to verify the correctness of the control method.

[0098] The invention discloses a space debris lateral angular velocity suppression and spin direction control method, that is, a space debris lateral angular velocity suppression and spin direction control method...

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Abstract

The invention provides a space debris lateral angular velocity suppression and spin direction control method. The space debris lateral angular velocity suppression and spin direction control method includes the following steps that firstly, a dynamical equation is derived; secondly, a controller is designed; thirdly, stability of the controller is analyzed; and fourthly, numerical value simulationverification is carried out. Through the steps, the target satellite attitude dynamical equation derived in the first step and the tension switching controller designed in the second step are combined to obtain the control method of restraining the transverse angular velocity of a target satellite, and a tether vibration dynamical equation derived in the second step and a PD controller designed in the third step are combined to obtain the method for controlling swinging and vibrating of a tether. According to the space debris lateral angular velocity suppression and spin direction control method, through switching control of two constant tension parts, the lateral angular velocity of the target satellite can be suppressed through the designed switching controller, and swinging and vibrating of the tether can be controlled by using a simple PD control law; the numerical value simulation is carried out in the fourth step, and thus feasibility and correctness of a control system are verified; and swinging and vibrating of the tether can be effectively suppressed while the lateral angular velocity of the target satellite can be suppressed.

Description

【Technical field】 [0001] The invention provides a space debris lateral angular velocity suppression and spin direction control method, which is a space debris lateral angular velocity suppression and spin direction control method using a space rope net system, which relates to a space capture system using a space rope net system The method of suppressing the transverse angular velocity and controlling the spin direction after the debris, which realizes the elimination of the transverse angular velocity and the control of the spin direction of the captured space debris through switching control of two constant tether tensions. The invention belongs to the technical field of tethered satellites in aerospace engineering. 【Background technique】 [0002] As the number of man-made space vehicles increases, limited orbital resources are occupied. After a satellite completes its mission, or runs out of fuel or malfunctions, it becomes useless and becomes space junk. If no correspo...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/66
CPCB64G1/24B64G1/66B64G1/245
Inventor 饶海平钟睿孙鑫贾英宏金磊
Owner BEIHANG UNIV
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