Flight control method based on inertial navigation/flight control system information fusion

Abstract

The invention relates to a flight control method based on inertial navigation/flight control system information fusion, which belongs to the field of information fusion control methods, and is used for solving the problem that the aircraft control performance is reduced or uncontrollable due to the fact that an attack angle, a sideslip angle and a vacuum speed cannot be measured in a complex flight environment. The method comprises the following steps of firstly, considering that a system attack angle, a sideslip angle and a vacuum speed are unmeasurable, introducing inertial navigation systeminformation as measurement information, establishing a system state equation and a measurement equation based on a kinetic model, and realizing estimation of the attack angle, the sideslip angle andthe vacuum speed through an extended Kalman filter, converting the six-degree-of-freedom nonlinear kinetic model of the aircraft into a strict feedback form, and designing a controller based on a backstepping method framework and a state estimation value, and finally, returning the control input to the aircraft kinetic model to realize tracking control. According to the method, inertial navigation/flight control system information fusion and flight control design are organically combined, and an effective way is provided for flight control system design under the condition that partial statesof the system are unmeasurable.

Description

technical field [0001] The invention relates to a flight control method, in particular to a flight control method based on information fusion of an inertial navigation / flight control system, and belongs to the field of information fusion control methods. Background technique [0002] The design of the flight control system is an important basis for ensuring the safe flight of the aircraft. Both classical control methods and intelligent control methods are widely used in the design of the flight control system. However, the premise of the application of these control methods is that the system state is required to be measurable or obtainable. However, in practical systems, some system states are not easy to measure directly, or due to the economic and performance limitations of measuring equipment, it is impossible to actually obtain all the state vectors of the system, thus affecting the control performance. Linear state observers can be used to solve the problem of unmeasur...

AI Technical Summary

Problems solved by technology

[0005] In order to avoid the deficiencies of the prior art, the present invention proposes a flight control method based on information fusion of the inertial navigation / flight control system to solve the problems caused by the inability to measure the angle of attack, sideslip angle and true airspeed in complex flight environments. Control degraded or uncontrollable issues

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