TECHNICAL BASIS - Spacecraft relative motion is affected by atmospheric drag through
predominantly along-track differential acceleration (along the satellites’ orbital direction of
motion), that can be modified by varying the individual satellites’ cross-wind surface area. At the
end of the period of performance, the first of two identical spacecraft will be completed. In the
future, the two satellites, controlled relative to each other using drag, will be able to collect
measurements at two different, known, and controlled locations on the orbit (<500-600 km, low
eccentricity, any inclination) to provide the first measurements of high atmospheric winds as
well as ions and neutral densities. Time series will be used for drag prediction in nominal
conditions, while a novel technique to detect sudden changes in density will be devised, based on
the idea that a drag modification can be treated as maneuver acting on the spacecraft.
EXPECTED RESULTS -
1) A forecasting technique to predict spacecraft drag along N future orbits, in nominal condition;
2) a maneuver detection technique, to determine any atmospheric sudden changes;
3) a WINCS designed to fit in a 1U CubeSat, and its complete on-the-ground testing;
4) a 2U CubeSat hosting WINCS and a deployable system to control its drag force;
4) the final product (hardware & software) will serve as proof of feasibility to extend the concept
for a future second spacecraft and to plan a two-satellite experimental flight.