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.
Method for motion control of solar sail spacecraft with reflectivity control devices in case of Earth–Mars flight
XLV ACADEMIC SPACE CONFERENCE, DEDICATED TO THE MEMORY OF ACADEMICIAN S.P. KOROLEV AND OTHER OUTSTANDING NATIONAL SCIENTISTS — PIONEERS OF SPACE EXPLORATION ; 2021 ; Moscow, Russia
AIP Conference Proceedings ; 2549 , 1
20.07.2023
8 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Look-ahead flight path control for solar sail spacecraft
Online Contents | 2013
|Look-ahead flight path control for solar sail spacecraft
SAGE Publications | 2013
|