Method for motion control of solar sail spacecraft with reflectivity control devices in case of Earth–Mars flight

The spatial heliocentric flight Earth–Mars of a non-perfectly reflecting solar sail spacecraft is considered. Thin-film control devices located along the perimeter of the solar sail are proposed as a control element. These spatial orientation controls are capable of changing their reflective charact...

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Bibliographic Details
Main Author: Khabibullin, R. M.
Format: Conference Proceeding
Language:English
Subjects:
Algorithms
Control equipment
Earth
Flight
Motion control
Reflectance
Solar sails
Spacecraft
Thin films
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Summary:The spatial heliocentric flight Earth–Mars of a non-perfectly reflecting solar sail spacecraft is considered. Thin-film control devices located along the perimeter of the solar sail are proposed as a control element. These spatial orientation controls are capable of changing their reflective characteristics depending on the voltage applied to them. A mathematical model of the photon pressure on the non-perfectly reflecting surface of the solar sail is described, taking into account the functioning of thin-film reflectivity control devices. An algorithm for generating a program for the nominal motion control of a solar sail spacecraft with and without thin-film control devices is described. The results of the Earth–Mars flight of a solar sail spacecraft have been obtained.
ISSN:0094-243X
1551-7616
DOI:10.1063/5.0107853