Design and simulation verification of aircraft altitude control based on pitch angle estimation

Abstract

In the conventional aircraft attitude control, the pitch angle is usually used as the inner loop to complete the control of the longitudinal channel. However, when the pitch angle sensor fails and its measurement data is unreliable, how to use a certain algorithm to ensure the effective control task of the attitude control loop. In this paper, a filtering algorithm based on pitch angle estimation is proposed to solve the shortcomings of aircraft in safety and reliability when the conventional altitude is controlled by pitch angle signal. The algorithm design and simulation results show that the filtering algorithm based on pitch angle estimation can effectively complete the control task and ensure better control quality.