Session
Poster Session 1
Abstract
The steadily increasing number of actors in space has made orbital debris mitigation increasingly important and has fueled the demand for innovative attitude and orbit control solutions. To meet this demand, the University of Florida Advanced Autonomous Multiple Spacecraft (ADAMUS) lab has developed a Drag De-Orbit Device (D3) for CubeSats to facilitate aerodynamically based orbital maneuvering, collision avoidance, and controlled re-entry as well as 3-axis attitude stabilization using aerodynamic and gravity gradient torques. A 2U CubeSat and mission is being designed to validate the D3 device and control algorithms developed by the ADAMUS lab. Tests of the orbital maneuvering and collision avoidance algorithms will commence after satellite deployment from the ISS, de-tumble, D3 boom deployment, and communication with the ground. The targeted de-orbit algorithm will then steer the satellite to a re-entry location visible by a radar station. The radar tracking data along with GPS telemetry will be utilized to characterize the performance of the D3 system and control algorithms, update re-entry aero-thermodynamic models, and gauge the effectiveness of atmospheric density estimation techniques. This paper details the designs of the D3 device, GNC algorithms, and complete CubeSat, and discusses the expected mission results.
CubeSat Mission to Demonstrate Aerodynamically Controlled Re-Entry using the Drag De-Orbit Device (D3)
The steadily increasing number of actors in space has made orbital debris mitigation increasingly important and has fueled the demand for innovative attitude and orbit control solutions. To meet this demand, the University of Florida Advanced Autonomous Multiple Spacecraft (ADAMUS) lab has developed a Drag De-Orbit Device (D3) for CubeSats to facilitate aerodynamically based orbital maneuvering, collision avoidance, and controlled re-entry as well as 3-axis attitude stabilization using aerodynamic and gravity gradient torques. A 2U CubeSat and mission is being designed to validate the D3 device and control algorithms developed by the ADAMUS lab. Tests of the orbital maneuvering and collision avoidance algorithms will commence after satellite deployment from the ISS, de-tumble, D3 boom deployment, and communication with the ground. The targeted de-orbit algorithm will then steer the satellite to a re-entry location visible by a radar station. The radar tracking data along with GPS telemetry will be utilized to characterize the performance of the D3 system and control algorithms, update re-entry aero-thermodynamic models, and gauge the effectiveness of atmospheric density estimation techniques. This paper details the designs of the D3 device, GNC algorithms, and complete CubeSat, and discusses the expected mission results.
