ATTITUDE CONTROL OF MULTIPLE RIGID BODY SPACECRAFT WITH FLEXIBLE HINGE JOINTS


Akbulut B., ÖZGÖREN M. K. , TEKİNALP O.

20th AAS/AIAA Spaceflight Mechanics Meeting, California, Amerika Birleşik Devletleri, 14 - 18 Şubat 2010, cilt.136, ss.2477-2478 identifier

  • Cilt numarası: 136
  • Basıldığı Şehir: California
  • Basıldığı Ülke: Amerika Birleşik Devletleri
  • Sayfa Sayıları: ss.2477-2478

Özet

Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Proper metrics such as accuracy, jitter and stability are used to evaluate the pointing performance of two control schemes: quaternion feedback controller, and linear quadratic regulator. Simulation results are given and discussed.