Identification and optimization of aircraft dynamics.

A technique is described for the design of an adaptive controller for multivariable systems and is based on recently developed methods for identification and optimization. An application of the method to a helicopter system with time-varying parameters is considered in detail. The response of the adaptive system is compared with the corresponding response of a system with a fixed controller and a system using optimal control. The comparison reveals the almost optimal character of the adaptive system. Nomenclature A = n X n, system matrix B = n X m, input matrix C = n X n, model matrix F = m X n, feedback matrix G — n X n, model matrix (estimate of A) H = n X m, model matrix (estimate of B) K = n x n, symmetric Riccati matrix P = n X n, symmetric positive definite matrix used in the model Q, S — n X n, symmetric positive semidefinite matrices of the performance index Qi = n X n, symmetric positive definite Lyapunov matrix R = m X m, symmetric positive definite matrix of the