ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT


Atas O., TEKİNALP O.

27th AAS/AIAA Space Flight Mechanics Meeting, San-Antonio, Northern Mariana Islands, 5 - 09 February 2017, vol.160, pp.2201-2212 identifier

  • Publication Type: Conference Paper / Full Text
  • Volume: 160
  • City: San-Antonio
  • Country: Northern Mariana Islands
  • Page Numbers: pp.2201-2212
  • Middle East Technical University Affiliated: Yes

Abstract

Propelling a spacecraft by using solar radiation pressure is examined in the context of orbital maneuvers. A locally optimal steering law to progressively change number of selected orbital elements together is addressed. An Earth centered cubesat satellite with solar sail is used as an example. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for Earth orbiting satellites. The satellite attitude control is realized using to-go quaternion feedback control. And the effectiveness of the approach to progressively changing the orbital parameters is demonstrated.