Optimal Control Methods For Missile Evasion
Abstract
Optimal control theory is applied to the study of missile evasion, particularly in the case of a single pursuing missile versus a single evading aircraft. It is proposed to divide the evasion problem into two phases, where the primary considerations are energy and maneuverability, respectively. Two problems are proposed as surrogates for the energy phase; a fixed final time problem with free final state and a free final time problem with fixed final state. These two optimal control problems are studied under several different scenarios regarding assumptions about the pursuer. First, a suboptimal control strategy, proportional navigation, is used for the pursuer. Second, it is assumed that the pursuer acts optimally, requiring the solution of a two-sided optimal control problem, otherwise known as a differential game. The resulting trajectory is known as a minimax, and it can be shown that it accounts for uncertainty in the pursuers control strategy. Finally, a pursuer whose motion and state are uncertain is studied in the context of Receding Horizon Control and Real Time Optimal Control. The results highlight how updating the optimal control trajectory reduces the uncertainty in the resulting miss distance.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2017
- Accession Number
- AD1055573
Entities
People
- Ryan W. Carr
Organizations
- Air Force Institute of Technology