A method comprising: receiving, via a processor, a plurality of Radar Cross Section measurements of a space object from a ground-based radar having a field of view, wherein the Radar Cross Section measurements are obtained from a plurality of passes of the space object into the field of view; characterized by estimating, via the processor, a first expected Radar Cross Section value based on the Radar Cross Section measurements when the space object is within the field of view at a first elevation angle relative to the radar, and a second expected Radar Cross Section value based on the Radar Cross Section measurements when the space object is within the field of view at a second elevation angle relative to the radar, wherein the first elevation angle is greater than the second elevation angle; determining, via the processor, a Stability Index based on the first expected Radar Cross Section value and the second expected Radar Cross Section value, wherein the Stability Index characterizes the attitude stability of the space object; receiving, via the processor, a Radar Cross Section measurement from the radar when the space object is within the field of view at the first elevation angle or the second elevation angle, wherein the Radar Cross Section measurement is received after the Stability Index has been determined; inputting, via the processor, the Stability Index into a Finite State Machine after the Stability Index is updated based on the Radar Cross Section measurement being slidably windowed, wherein the Finite State Machine tracks the space object between a plurality of states; and taking, via the processor, an action based on a change detected in one of the states. receiving, via a processor, a plurality of Radar Cross Section measurements of a space object from a ground-based radar having a field of view, wherein the Radar Cross Section measurements are obtained from a plurality of passes of the space object into the field of view; characterized by estimating, via the processor, a first expected Radar Cross Section value based on the Radar Cross Section measurements when the space object is within the field of view at a first elevation angle relative to the radar, and a second expected Radar Cross Section value based on the Radar Cross Section measurements when the space object is within the field of view at a second elevation angle relative to the radar, wherein the first elevation angle is greater than the second elevation angle; determining, via the processor, a Stability Index based on the first expected Radar Cross Section value and the second expected Radar Cross Section value, wherein the Stability Index characterizes the attitude stability of the space object; receiving, via the processor, a Radar Cross Section measurement from the radar when the space object is within the field of view at the first elevation angle or the second elevation angle, wherein the Radar Cross Section measurement is received after the Stability Index has been determined; inputting, via the processor, the Stability Index into a Finite State Machine after the Stability Index is updated based on the Radar Cross Section measurement being slidably windowed, wherein the Finite State Machine tracks the space object between a plurality of states; and taking, via the processor, an action based on a change detected in one of the states.