Flexible Aircraft Attitude Control Method with the Measurement of Angular Acceleration

doi:10.3969/j.issn.1000-1093.2020.11.009

Abstract

Abstract: The attitude control of slender flexible aircraft outside the atmosphere is discussed. The essence of the problem is to control the attitude tracking command of rigid body under the condition of additional flexibility of measuring device. A dynamic surface attitude control method is presented for attitude command tracking. A second-order dynamic model of flexible deformation is established. A nonlinear model is established by combining the angular velocity of rigid body with the flexible deformation, and the Kalman filter is designed. The measurement of angular accelerometer is introduced for the problem of disturbance torque caused by the factors, such as the centroid shift of rail-controlled engine. After notch filtering, the estimated torque of each axis is obtained and used as the input of Kalman filter. The simulated results show that, for the flexible air vehicle, the proposed state estimation and control method can ensure the attitude tracking error being within 0.5°.

Key words: flexibleairvehicle, dynamicsurfacecontrol, Kalmanfilter, angularaccelerometer, notchfilter

CLC Number:

V448.22⁺2

ZHANG Bolun， ZHOU Di. Flexible Aircraft Attitude Control Method with the Measurement of Angular Acceleration[J]. Acta Armamentarii, 2020, 41(11): 2225-2233.

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第41卷第11期2020 年11月
兵工学报ACTA ARMAMENTARII
Vol.41No.11Nov.2020

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