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A tether release stability control method and an electric power tether last stage off-track stability control method

A stable control method and electrodynamic technology, applied in the general control system, control/regulation system, adaptive control, etc., can solve problems such as complex balance motion and rope vibration, difficult electrodynamic rope, small damping, etc., and achieve balance Dynamic and rope vibration suppression, robustness, and the effect of maintaining a stable system attitude

Active Publication Date: 2017-04-05
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

However, because the tether has the characteristics of small damping and high flexibility, complex balance motion and tether vibration problems are easily generated during the release stage and the system de-orbiting stage due to the influence of the space environment perturbation and the rocking of the final stage of the rocket. , which leads to the control of the electric power rope in the release and derailment stages is a difficult point of this technology
[0003] According to the retrieval of related literature at home and abroad, there is no relevant literature in the searched literature that is closely related to this technology

Method used

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  • A tether release stability control method and an electric power tether last stage off-track stability control method
  • A tether release stability control method and an electric power tether last stage off-track stability control method
  • A tether release stability control method and an electric power tether last stage off-track stability control method

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Embodiment Construction

[0042] The invention can be applied to the abandoned aircraft based on the electric power tether to solve the system stability control problem in the process of its derailment.

[0043] The rocket final stage deorbit system based on electric power tether includes a tether as a conductor (conductive tether), a passive charge collector, and an electron emission device. The working principle of the system can be described as: the last stage of the rocket first uses the terminal load to release and deploy the tether. After the deployment is completed, the last stage of the rocket drags the conductive tether to move in the geomagnetic field at orbital speed, and induces an electromotive force on the tether. The charged particles (usually electrons) in the ionosphere are collected by the passive charge collector at the top of the tether, and emitted by the electron emission device at the end of the tether to form a stable current. The action creates the Lorentz force, the electrodyn...

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Abstract

The invention provides a rope system releasing stable control method and an electric force rope system off-tracking stable control method. The rope system releasing stable control method comprises the following steps: (1) based on a non-linear optimal control theory, determining a control variable and a state variable aiming at different processes, namely a rope system releasing process or an electric force auxiliary off-tracking process; establishing an open ring optimal control model; considering task restriction and solving an open ring optimal control rule through a pseudo-spectrum optimization algorithm; (2) designing a robust feedback controller based on a trace tracking concept by taking a solved open ring optimal trace as a reference trace, wherein a feedback control grain is commonly determined by an open ring optimal control algorithm and a numerical value interpolation. According to results of the step (1) and the step (2), a control method of a rope system releasing process and the electric force auxiliary off-tracking process is determined.

Description

technical field [0001] The invention relates to a method for controlling de-orbiting of the last stage of a rocket based on an electric power rope, and belongs to the technical field of removing abandoned satellites and final stages of rockets. Background technique [0002] The deorbiting technology of rocket final stage based on electric power rope is a novel deorbiting method. Its basic principle is that when the conductive tether moves in the earth’s magnetic field, an electromotive force will be generated in the tether due to cutting the magnetic field line. When the tether and When the free electrons and ions in the atmospheric ionosphere form a closed loop, a current can be generated in the tether, and the interaction between the current and the Earth's magnetic field will generate a Lorentz force on the tether. The Lorentz force is opposite to the motion direction of the final stage of the rocket, forming resistance. Compared with the traditional method of using prop...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10G05B13/04
Inventor 张烽王小锭申麟张旭辉焉宁李扬高朝辉王书廷
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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