Adaptive fault tolerant control method considering input constraints of actuator for hypersonic flight vehicle

Abstract

The invention relates to an adaptive fault tolerant control method considering input constraints of an actuator for a hypersonic flight vehicle. The method comprises the following steps of firstly, establishing a standard longitudinal dynamics model of the hypersonic flight vehicle and decomposing the model into speed, height and attitude subsystems; secondly, establishing an air vehicle actuatorfault model with generality, and compensating input constraint characteristics of the actuator by constructing a smoothing function; and thirdly, respectively designing an adaptive compensation controller and an adaptive law for three subsystems through a dynamic inverse method, a backstepping method and a sliding mode control method. According to the method, the stability of longitudinal model parameters such as air vehicle speed, height and the like is guaranteed in a level flight working state when the hypersonic flight vehicle with the input constraint characteristics of the actuator has an actuator fault, and the method has the advantages of strong fault-tolerant capability and robustness to external disturbance and the like.

Description

technical field [0001] The invention relates to an adaptive fault-tolerant control method for a hypersonic aircraft considering actuator input constraints, which is mainly used for height and speed tracking when an actuator failure occurs when a hypersonic aircraft is operating in a level flight section and has actuator input constraint characteristics Control belongs to the technical field of aircraft control. Background technique [0002] Hypersonic vehicles have attracted significant commercial and military attention in recent years as a reliable and economical means of transportation to adjacent space. However, due to its special structure and unique flight conditions, hypersonic vehicles are extremely sensitive to aerodynamic parameters and their dynamic characteristics are highly nonlinear. All of these factors make the control design of hypersonic vehicles very difficult compared with traditional aircraft. [0003] So far, control methods including robust control, s...

AI Technical Summary

Problems solved by technology

[0004] The problem to be solved by the technology of the present invention is: because the hypersonic vehicle may be affected by various disturbance factors during flight, which may lead to various failures of the elevator, and the hypersonic vehicle may have actuator input constraint characteristics, the present invention provides a consideration The hypersonic vehicle adaptive fault-tolerant control method with actuator input constraints solves the impact of various elevator failures and actuator input constraints on the aircraft during the flight of the hypersonic vehicle, ensuring the fault tolerance and robustness of the system

Images