Session
Session V: Guidance and Control
Abstract
Missions that want to maintain specific separation distances have previously relied on propulsion systems or aerodynamic actuators to compensate for differential drag effects. These systems can be complex and resource consuming for resource constrained missions like SmallSats. For example, the SCintillation and Ionospheric Occultation Nanosats (SCION) mission requires separation distances between its two 1U CubeSat spacecraft on the order of 10 km for at least 90 days. Ensemble runs on an orbit propagator that models aerodynamic drag demonstrate the validity of alternatives to propulsive and actuator-based separation control such as coarse attitude control and spin-averaged drag matching to meet such requirements. Initial results suggest that separation distances less than 1 km are possible at least 10 days into the mission and further simulations will demonstrate the potential to restrict separation distance for even longer periods of time.
Simulation Results of Alternative Methods for Formation Separation Control
Missions that want to maintain specific separation distances have previously relied on propulsion systems or aerodynamic actuators to compensate for differential drag effects. These systems can be complex and resource consuming for resource constrained missions like SmallSats. For example, the SCintillation and Ionospheric Occultation Nanosats (SCION) mission requires separation distances between its two 1U CubeSat spacecraft on the order of 10 km for at least 90 days. Ensemble runs on an orbit propagator that models aerodynamic drag demonstrate the validity of alternatives to propulsive and actuator-based separation control such as coarse attitude control and spin-averaged drag matching to meet such requirements. Initial results suggest that separation distances less than 1 km are possible at least 10 days into the mission and further simulations will demonstrate the potential to restrict separation distance for even longer periods of time.
