Synthesis of Aircraft Modal Control Systems

Abstract

The recently developed theory of modal control has so far been mainly applied to the design of process control systems. This theory is, however, capable of much wider application and it is the principal object of this paper to illustrate its use as a basis for the synthesis of aircraft control systems. The particular illustrative problem considered is that of synthesising a lateral autopilot for bank-angle and roll-rate mode control. Typical aerodynamic data for an aircraft flying at M=0·9 and at altitudes from sea level to 40 000 ft (12 km) are used in the calculations.