Synthesis of aircraft heading control taking into account inertia

Аuthors

Alesov M. B.

Company "Ramenskoye Design Company", 2, Guriev str., Ramenskoye, Moscow Region, 140103, Russia

e-mail: mbalesov@spb.rpkb.ru

Abstract

The problems of synthesizing inertial heading control of the trajectory movement of an air-craft when turning to a set heading angle and when directly pointing the aircraft at a target navigation point are considered. Inertia is taken into account using integral block. The necessary conditions for minimum time optimality determine that the roll angle function has "trapezoidal" or "tri-angular" shape when performing the maneuver. Analytical expressions of the heading angle, as well as formulas for calculating the timing of control switching and characteristic values of the phase variable, were obtained. Examples of calculation of inertial control and numerical modeling of aircraft trajectories for two pathing control tasks are presented.

Keywords:

synthesis of trajectory control of aircraft; pathing motion control method; polar coordinate system; Picard method; Fresnel integral; inertial control

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