A Heading and Flight-Path Angle Control of Aircraft Based on Required Acceleration Vector

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  • 必要加速度ベクトルに基づいた，航空機の方位角・経路角制御の一方法
  • ヒツヨウ カソクド ベクトル ニ モトヅイタ コウクウキ ノ ホウイカク ケイロカク セイギョ ノ イチ ホウホウ

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This paper describes a control of heading and flight-path angles of aircraft to time-varying command angles. The controller first calculates an acceleration command vector (acV), which is vertical to the velocity vector. acV consists of two components; the one is feedforward acceleration obtained from the rates of command angles, and the other is feedback acceleration obtained from angle deviations by using PID control law. A bank angle command around the velocity vector and commands of pitch and yaw rates are then obtained to generate the required acceleration. A roll rate command is calculated from bank angle deviation. Roll, pitch and yaw rate commands are put into the attitude controller, which can be composed of any suitable control laws such as PID control. The control requires neither aerodynamic coefficients nor online calculation of the inverse dynamics of the aircraft. A numerical simulation illustrates the effects of the control.

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