The simulation program ran from the missile mid-course guidance to flight termination. The mid-course guidance pitch control used singular perturbation techniques. The yaw control channel used proportional navigation. A 3-state Kalman filter provided the input to the guidance law. The guidance law was a 3-state optimal guidance law. This law used angle range and doppler filter. The autopilot was an acceleration autopilot. The guidance update rates and mid-course estimator (kalman filter) update rates were 10 Hz. The terminal estimation and guidance rates were 40Hz.
[[OGLI Algorithm Verification]] – Ada algorithm differed from FORTRAN sim
- lucianoDevelopingMissileGuidance1989