Aircraft attitude control method and device and electronic equipment

Abstract

The invention provides an aircraft attitude control method and device and electronic equipment, and the method comprises the steps: determining a state feedback control law mathematical model based on a first attitude control mathematical model represented according to a preset format in a pre-obtained nonlinear mathematical model; determining an attitude controller mathematical model containing a fractional order differential item by adopting a sliding mode control mode based on a pre-obtained sliding mode surface control mathematical model; substituting attitude controller parameter items in the state feedback control law mathematical model, and determining an aerodynamic torque coefficient based on a pre-acquired system control quantity mathematical model and a current state value of the aircraft; calculating a rudder deflection control instruction based on the aerodynamic torque coefficient; and controlling the attitude of the aircraft based on the rudder deflection control instruction. The attitude controller mathematical model determined by the method comprises a fractional order differential item, so that the rudder can provide a large control quantity at the beginning, the rapidity and accuracy of an aircraft attitude control system are improved, and the convergence time of the aircraft attitude is shortened.

Description

technical field [0001] The present invention relates to the technical field of attitude control, in particular to an aircraft attitude control method, device and electronic equipment. Background technique [0002] Flight Control System (FCS), as one of the important subsystems of a hypersonic vehicle, is an important guarantee for a hypersonic vehicle to successfully complete its flight mission. One of the core and key technologies in The task of the hypersonic aircraft attitude control system is: to design the commands of the aircraft actuators, so that the attitude of the aircraft can quickly and accurately track the command signals given by the guidance system, and at the same time ensure the stability of the aircraft under various uncertainties and external disturbances. , a high-precision attitude control system is a necessary guarantee for the aircraft to achieve stability and complete flight missions. In a related technology, the fixed-time convergent control law de...

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Problems solved by technology

In a related technology, the fixed-time convergent control law designed based on the time-varying sliding mode method is applied to the attitude control of the aircraft loading section, and the system trajectory is placed on the zero-sliding mode surface at the initial moment by adding a time-varying term , to ensure the global robustness of the attitude control system. However, when the set convergence time is relatively short, the demand for control force is relatively large in a certain period of time, which may exceed the physical limit of the aircraft and cannot achieve precise control. Purpose

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