公开(公告)号：US20230026233A1

公开(公告)日：2023-01-26

申请号：US17757357

申请日：2020-11-26

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Youngshin KANG ,  Am CHO ,  Bumjin PARK ,  Seongwook CHOI ,  Sam Ok KOO ,  Chang Sun YOO ,  Yushin KIM

IPC: B64C27/56 ,  B64D27/24 ,  B64C11/30 ,  B64C27/32

Abstract: 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.

公开(公告)号：US20240166333A1

公开(公告)日：2024-05-23

申请号：US18511423

申请日：2023-11-16

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Youngshin KANG ,  Am CHO ,  Seongwook CHOI ,  Yushin KIM ,  Jongmin BAE ,  Junho CHO ,  Haneul YUN ,  Myeong Kyu LEE

IPC: B64C11/30 ,  B64C13/50 ,  B64D35/04

CPC classification number: B64C11/305 ,  B64C13/503 ,  B64D35/04 ,  B64C27/52

Abstract: 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.

公开(公告)号：US20200278701A1

公开(公告)日：2020-09-03

申请号：US16872825

申请日：2020-05-12

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Youngshin KANG ,  Am CHO ,  Seongwook CHOI ,  Yushin KIM ,  Sung Ho CHANG

IPC: G05D1/10 ,  B64C29/00 ,  B64C27/82 ,  B64C19/00 ,  B64C13/02

Abstract: 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.