A tether dragging control method and system for a failed satellite carrying a solar panel

Abstract

The invention discloses a tether dragging control method and system for an out-of-service satellite carrying a solar sail. Aiming at the sail board vibration problem that may occur during the out-of-orbit process of an out-of-service satellite carrying a solar sail, a sufficient method is proposed. The tether dragging control method considering the flexibility of the sailboard belongs to the field of spacecraft attitude dynamics and control. The invention can well reflect the influence of the vibration of the solar sail plate, and the control method effectively reduces the vibration amplitude of the solar sail plate in the dragging process. The actuator on the main satellite outputs the required constant tension and applies it to the failed satellite carrying the solar panel to suppress the vibration of the solar panel of the failed satellite during the towing process. The invention is used to control the vibration of the sail plate in the process of dragging and de-orbiting after the failed satellite carrying the solar sail plate is captured by flying net, and provides technical support for cleaning up large-scale failed satellites in space.

Description

technical field [0001] The invention relates to a tether dragging control method and system for a failed satellite carrying a solar sail, and belongs to the technical field of spacecraft attitude dynamics and control. Background technique [0002] Geostationary Orbit (GEO) plays an important role in communication, navigation, early warning, remote sensing and other fields. At present, there are about 2,600 individual satellites (including normal working and failed spacecraft) distributed in orbit, and most of them are concentrated over the continents where human activities are intensive. With the increasing number of spacecraft, GEO orbital resources are becoming more and more scarce. In order to ensure the sustainable development of space activities, the failed spacecraft should be removed in time to provide a safe and stable orbital environment for satellites in orbit. [0003] Tethered towing system, which connects the main satellite and the invalid space satellite throu...

AI Technical Summary

Problems solved by technology

[0004] In the prior art, the solar panels of the failed satellites are treated as rigid bodies without considering their flexibility characteristics, which has limited influence on the failed satellites with smaller solar panels, but for the failed satellites with larger solar panels, dragging During the process, the relatively large vibration of the solar panel due to its flexible characteristics will have a great impact on the safety and stability of the system

In addition, the existing tether dragging control method adopts a time-varying tension control method during the dragging process of the failed satellite, and the continuous change of tension will excite the vibration of the sail panel of the failed satellite.

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