Extended-State-Observer-Based Angular Acceleration Estimation for Supersonic Aircraft Lateral–Directional Control

Abstract

Large-slenderness-ratio (LSR) aircraft exhibit more severe lateral–directional coupling compared with other aircraft, which poses a significant challenge to their flight safety, especially during high-speed maneuvers. Reliable attitude decoupling control is, therefore, essential for LSR aircraft. In this study, a novel control framework that combines incremental nonlinear dynamic inversion (INDI) and extended state observer (ESO) is proposed for supersonic roll maneuver control of LSR aircraft. The ESO is used to estimate the angular acceleration on the basis of an onboard mathematical model. The acceleration estimator based on ESO achieves superior noise reduction compared with the complementary filter (CF) and reduces the onboard model requirement without significantly sacrificing estimation accuracy. Monte Carlo (MC) simulations and frequency–domain analysis demonstrate the effectiveness and robustness of the proposed controller. The sensitivity of parameter uncertainties is also investigated, revealing that the natural frequency of the actuator is the most critical parameter affecting robustness. Finally, flight tests validate the effectiveness of the proposed control structure.

Control Design for Soft Transition for Landing Preparation of Light Compound-Wing Unmanned Aerial Vehicles Based on Incremental Nonlinear Dynamic Inversion

“…Lyu et al [30] proposed a new framework for supersonic roll maneuver control that combines INDI and extended state observer (ESO). ESO reduces command oscillations and improves the servo's working life.…”

“…The pitch angle rate loop is responsible for controlling the pitch angular rates, as the main control objectives. It is controlled using INDI+ESO [30]. The overall control structure is shown in Figure 7.…”

“…The gain in the control law can be determined by adjusting parameters, which requires sufficient experimentation and iteration. We chose to fine tune based on previous relevant research [30] and determined that the gains r K , e K , and h K are 7, 70, and 0.11, . θ can be regarded as the desired change rate of the pitch angle.…”

“…The gain in the control law can be determined by adjusting parameters, which requires sufficient experimentation and iteration. We chose to fine tune based on previous relevant research [30] and determined that the gains For the control assignment section, how the pitch rate command The control structure consists of four key components: reference model, error controller, ESO, and control allocation.…”