ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT


Atas O., TEKİNALP O.

27th AAS/AIAA Space Flight Mechanics Meeting, San-Antonio, Kuzey Mariana Adaları, 5 - 09 Şubat 2017, cilt.160, ss.2201-2212 identifier

  • Cilt numarası: 160
  • Basıldığı Şehir: San-Antonio
  • Basıldığı Ülke: Kuzey Mariana Adaları
  • Sayfa Sayıları: ss.2201-2212

Özet

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.