A Nonlinear Aircraft Track Control Method

Abstract

The invention provides a nonlinear aircraft flight path control method. A flight path instruction generator sends a flight path instruction signal to an outer ring flight path controller; the outer ring flight path controller receives the flight path instruction and the aircraft position, the velocity, the flight path inclination and the flight path azimuth signals measured by the sensor, and calculates and sends an engine throttle instruction signal to an aircraft platform and sends an attack angle instruction, a sideslip angle instruction and a rolling around velocity vector roll angle instruction signal to an inner ring attitude controller; the inner ring attitude controller receives the attack angle instruction, the sideslip angle instruction, the rolling around velocity vector roll angle instruction signal and the aircraft attack angle, the sideslip angle, the rolling around velocity vector roll angle and the angular velocity signals measured by the sensor, and a rudder surface deflection instruction is calculated and sent to the aircraft platform; through measurement, the sensor acquires the aircraft parameter signals and feeds the signals back to the outer ring flight path controller and the inner ring attitude controller; and the aircraft receives a rudder deflection instruction to complete a corresponding rudder deflection action and receives a throttle control instruction to realize a corresponding thrust.

Description

technical field [0001] The invention belongs to the technical field of flight control of aviation aircraft, and in particular relates to a method for controlling a non-linear aircraft track. Background technique [0002] At present, the control law of aviation aircraft generally adopts linear gain scheduling control law. The design of this traditional control law based on small disturbance linearization in trim state and classical control theory is complicated, involving the selection of several working state points and the design of corresponding linear control law. The tuning of control parameters is cumbersome, and due to the inherent nonlinearity of aeronautical vehicles, the stability of the linear gain scheduling control law lacks sufficient theoretical guarantee. [0003] The nonlinear dynamic inverse control method based on time-scale separation is a nonlinear flight control method that has received widespread attention in recent years. Based on the time-scale separa...

AI Technical Summary

Problems solved by technology

However, the motion model of the center of mass of the aircraft is not an affine form, so the explicit solutions of the angle of attack command, the roll angle command around the velocity vector and the throttle command cannot be obtained directly, which limits the application of the feedback linearization control law design method

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