Autopilot Design Methodology for Bank-to-Turn Missiles.

摘要

Complete use of the multiinput/multioutput (MINO) capability of modern control theory is utilized by employing a 3-axis, fully coupled autopilot design for the extended medium range air-to-air technology (EMRAAT) airframe. With the exception of the drag equation, all nonlinear dynamics (including coriolis and gyroscopic terms) are retained prior to model linearization. Discrete linear quadratic regulator theory is used for controller designs. Gain scheduling is addressed in a stochastic manner allowing large random parameteric variations in missile roll, pitch, yaw rates, angle-of-attack, and sideslip. This is in contrast to most modern methodologies which in spite of the MIMO capability of modern control separate one axis from the other two (either roll from yaw/pitch or pitch from yaw/roll) in a decoupled design strategy.