Abstract
This paper presents a method of robust control system design for aircraft flight control systems with the existence of uncertainty parameters such as stability and control derivatives resulted by parameter identification process using real flight test data. A nonlinear model of aircraft turn coordination system is considered where the problem is to find the optimal controller by using the H∞ optimal control method combined with a quasi-Newton optimization method. The present method designs the gain of the cross pass channel for the aileron and rudder interconnect, which causes nonlinearity of the system. The robust controller design is qualified as designing the H∞ optimal control under a given value of the 'nonlinear' gain, and sequentially determining the optimal 'nonlinear' gain subject to minimize the error performance of the turn coordination system by using the quasi-Newton method. The perturbations of the uncertainties model have structured uncertainties constructed by the differences between the aerodynamic coefficients derived by parameter identification process and wind tunnel result. The proposed method is applied to the real flight test data of N250 PA-1 aircraft.
Highlights
The purpose of the design of the flight control system for the turn coordination system of an aircraft is to design control laws that determine controller such that the augmented system will allow roll command to perform steady bank angle while keep the lateral acceleration and yawing moment small
This paper presents a method of robust control system design for aircraft flight control systems with the existence of uncertainty parameters such as stability and control derivatives resulted by parameter identification process using real flight test data
A nonlinear model of aircraft turn coordination system is considered where the problem is to find the optimal controller by using the H∞ optimal control method combined with a quasi-Newton optimization method
Summary
The purpose of the design of the flight control system for the turn coordination system of an aircraft is to design control laws that determine controller such that the augmented system will allow roll command to perform steady bank angle while keep the lateral acceleration and yawing moment small. Matrix model of disturbance to state B1, matrices C1, D11, D12 mentions the output control model, matrix C2 explains the output control model, matrix D21 contains elements that represents a relationship between output control and disturbances, are more detailed by equations, while matrix D11 = 0 and matrix D22 = 0 In this model, it is assumed that the perturbations are included only in the plant and caused by the uncertainty in the coefficients of aerodynamics. The gain to be achieved corresponding to this output control has a structure as follows: where δ Acom and δRcom are the roll and yaw rate commands to the aileron and rudder, respectively, and δ ∆ is perturbation of ∆ AB that satisfies δ ∆ ∞ ≤ 1. The bank angle responses, on steady state of turn, to aileron deflection and sideslip angle are taken as the ideal models:
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