Korea Aerospace Research Institute

Youngshin Kang

Seongwook Choi

Yushin Kim

Am Cho

Bumjin Park

Jongmin Bae

Sung Ho Chang

Myeong Kyu Lee

Chang Sun Yoo

Junho Cho

Sungho Chang

Sam Ok Koo

Joowon Choi

Haneul Yun

The present invention relates to a control input device applicable to an eVTOL aircraft, which is an electric-powered vertical take-off and landing aircraft, and more particularly, to an aircraft control input device that may replace a cyclic control stick, a tail rotor control pedal, and a collective control stick used for flight control of a conventional aircraft, which is simpler in configuration and easier to operate than conventional control devices and may improve pilot convenience and stability of flight operation through simple and accurate flight manipulation, and a command input method using the same.

Aircraft control input device and command input method using the same

An apparatus for controlling a tilt rotor is provided. The apparatus includes a thrust command generator configured to generate a first collective pitch angle based on a throttle command, a rotation speed compensator configured to generate a compensation value based on a rotation speed of the motor, a compensation weight generator configured to generate weight values according to a flight speed, a collective pitch angle command generator configured to generate a collective pitch angle adjustment command of the rotor blade of the motor, based on the first collective pitch angle and a first compensation value being obtained by multiplying the compensation value by a preset conversion ratio and a first weight value, and a motor controller configured to generate a motor control command based on a second compensation value being obtained by multiplying the compensation value by a second weight value and the first collective pitch angle.

Method of controlling tilt rotor, apparatus for controlling tilt rotor, and aircraft including the apparatus

Provided is a system for controlling an RPM of a propeller and a rotor of a flight vehicle having multiple power units including: a collective pitch angle command generating unit generating a collective pitch angle command upon receiving a thrust control command from a pilot or an automatic controller; a disturbance factor compensating unit for generating an RPM compensation electronic speed control (ESC) command for compensating for an RPM error, and an electronic speed adjustment command generating unit generating a final ESC command upon receiving a collective command input or derived in the process of generating the collective pitch angle command by the collective pitch angle command generating unit and the RPM compensation ESC command generated by the disturbance factor compensating unit. RPMs of motors of a flight vehicle having a plurality of propellers and rotors may be maintained to be the same.

System for controlling propeller and rotor RPM of aerial vehicle having multiple power devices

Provided is a vertical take-off/landing aircraft controlling a tilt angle of a main rotor, based on a vertical posture control signal during low-speed flight, wherein, when an aircraft steering signal including a vertical posture control signal for changing the pitch posture angle of the vertical take-off/landing aircraft by a first pitch posture angle is obtained, a flight controller determines a tilt angle of the main rotor with reference to the first pitch posture angle and generates a tilt angle control signal for the main rotor based on the determined tilt angle.

Method and computer program for controlling tilt angle of main rotor on basis of pitch attitude control signal low-speed flight state, and vertical take-off and landing aircraft

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Daejeon, South Korea

Youngshin Kang