Session
Weekday Poster Session 4
Location
Utah State University, Logan, UT
Abstract
Since the early 2000s, the number of nanosatellites launched has shown an exponential trend. As Low Earth Orbit (LEO) is getting crowded with nanosatellites and small satellites, FCC's new "five-year rule" regulation requires space operators to plan disposal through re-entry into Earth's atmosphere in no more than five years after the mission's end. One was to decelerate and deorbit a satellite is by increasing the satellite drag area using active attitude control, which can be used to tactically deorbit satellites to satisfy the "five-year rule".
The atmospheric density in the upper atmosphere (LEO region) widely varies as a function of altitude, latitude, longitude, geomagnetic activity, solar cycle, seasons, and local time. One factor potentially within the control of the satellite operator is the drag associated with the satellite ram face. This is accomplished by controlling attitude which is especially effective for satellites with faces offering varying cross-sectional areas (e.g., 3U or 6U CubeSats).
In this paper, the authors present a feasibility study of how satellite drag can be predicted and controlled by managing the satellite attitude to increase or decrease the effective cross-sectional area of a satellite in consideration of variable factors, such as altitude, inclination, geomagnetic activity, solar cycle, variations in seasons, and local time.
An Evaluation of CubeSat Orbital Decay Utilizing ADCS
Utah State University, Logan, UT
Since the early 2000s, the number of nanosatellites launched has shown an exponential trend. As Low Earth Orbit (LEO) is getting crowded with nanosatellites and small satellites, FCC's new "five-year rule" regulation requires space operators to plan disposal through re-entry into Earth's atmosphere in no more than five years after the mission's end. One was to decelerate and deorbit a satellite is by increasing the satellite drag area using active attitude control, which can be used to tactically deorbit satellites to satisfy the "five-year rule".
The atmospheric density in the upper atmosphere (LEO region) widely varies as a function of altitude, latitude, longitude, geomagnetic activity, solar cycle, seasons, and local time. One factor potentially within the control of the satellite operator is the drag associated with the satellite ram face. This is accomplished by controlling attitude which is especially effective for satellites with faces offering varying cross-sectional areas (e.g., 3U or 6U CubeSats).
In this paper, the authors present a feasibility study of how satellite drag can be predicted and controlled by managing the satellite attitude to increase or decrease the effective cross-sectional area of a satellite in consideration of variable factors, such as altitude, inclination, geomagnetic activity, solar cycle, variations in seasons, and local time.
