Space Object Attitude Maneuver Indicator (SOAMI)

Providing an indication of satellite orbital maneuvers before they actually occur is critical for ensuring the safety and efficacy of space traffic management and domain awareness.  The developed algorithm is based on using light curve data to estimate an attitude maneuver that may be a precursor to an orbital maneuver.  The approach, called Space Object Attitude Maneuver Indicator (SOAMI), utilizes wavelet decomposition for identification of attitude slew maneuvers and changes in a satellite’s attitude, using the light curve, in real-time with no information about the reflection model.  Wavelet decomposition allows for identification of when the attitude slew maneuver occurs.  Other methods, such as those based on Fourier analyses, of attitude slew detection either do not allow for identification of when the maneuver occurred, or they do not allow for good time resolution.  The SOAMI algorithm has been verified using extensive simulation trials as well as real data of a satellite performing actual attitude maneuvers.  The proposed work involves a path of transitioning SOAMI by testing it in the Space Systems Command (SSC) Technology, Applications, and Process (TAP) laboratory.