Ước lượng các tham số ổn định và điều khiển của máy bay từ dữ liệu bay thử nghiệm

Abstract. Purpose of this paper is estimating aircraft stability and control parameters from flight test data by using two methods: Equation Error and Maximum Likelihood. A Matlab program is written for simulation studies in 6 degree-of-freedom nonlinear Aerosonde unmanned air vehicle model. The paper also presents advantages and disadvantages of each method. Flight test control inputs are conventional 3-2-1-1 square wave inputs and optimal inputs obtained from Bellman dynamic programming. Aerosim blockset is used in flight simulation with pseudo measurement noises to reduce the gap between pseudo flight data & real flight data.