Investigation into the Application of Dynamic Programming to Determine Optimal Controls for Tracking a Cruise Missile Maneuver by CMMCA (Cruise Missile Mission Control Aircraft)

摘要

This thesis investigated the application of dynamic programming to determine the optimal control inputs for tracking a cruise missile maneuver by the Cruise Missile Mission Control Aircraft (CMMCA). Conventional dynamic programming and state increment dynamic programming were considered. The objective was to minimize cruise missile deviations from a desired position within the radar sweep cone. Only single turning maneuvers of the cruise missile were investigated in this study. Implementation on a personal computer was attempted. Since time defined the stages for the dynamic programming method, the effect of different time increments was evaluated. The study found state increment dynamic programming difficult to implement. Problems were encountered in the processing of block boundaries. Memory limitations of the FORTRAN compiler prohibited implementation of the dynamic programming technique on the personal computer. The methodology was successfully implemented on a VAX running on the VMS operating system. The model, as formulated, was found to be extremely sensitive to the size of the time increments defining the stages. Widely different controls were computed using three different time increments. A 0.5 minute time increment was determined to provide the best results of the increments investigated. Keywords: Guided missile tracking optimization. Theses. (EDC)