Research Information System
AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022, California, United States Of America, 3 - 07 January 2022, (Full Text)
© 2022, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.Over the last few decades, target sets evaluated as threats by air defense systems have been expanding significantly. As a result, air defense systems are expected to defend against numerous targets where some of them has become increasingly hard to be detected and tracked. Uncertainties due to lack of target information, unpredictable target maneuvers, and coordination of targets lower the success of air defense systems as a whole due to the performance degradation of interceptors allocated to predefined targets in a one to one fashion. Utilizing interceptors’ kinematic capabilities in a coordinated manner to create a defended airspace is expected to be very effective against multiple targets where some of them may not even transform into eligible threats. However, kinematic capabilities (reachable set) of interceptors at any flight condition must be forecasted for such an approach to become applicable. In this paper, in order to generate reachable sets for an interceptor, the constrained model predictive control concept is employed by utilizing a nonlinear model, where variations in velocity (due to aerodynamic drag and thrust) and acceleration limits are not disregarded. Firstly, the problem of reachable set computation for the nonlinear system is solved by constrained model predictive programming with different desired final conditions. A much realistic reachable set calculation is carried out by including autopilot dynamics with bounded acceleration responses while enforcing a minimum total control command effort criterion to reach desired final conditions. Afterward, for different flight conditions and different flight durations, boundaries of the reachable set in terms of minimum and maximum ranges are obtained. Reachability boundaries related to kinematic conditions during the flight are to be extracted from a database embedded in a guidance computer, where the database is generated offline by the approach suggested in this paper.