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

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...

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

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